US3352494A - Supersonic jet propulsion nozzle - Google Patents

Supersonic jet propulsion nozzle Download PDF

Info

Publication number
US3352494A
US3352494A US474795A US47479565A US3352494A US 3352494 A US3352494 A US 3352494A US 474795 A US474795 A US 474795A US 47479565 A US47479565 A US 47479565A US 3352494 A US3352494 A US 3352494A
Authority
US
United States
Prior art keywords
nozzle
casing
throat
plug
downstream end
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US474795A
Inventor
Colville Francis Jeffrey
Roberts Norman
Brown David Morris
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Application granted granted Critical
Publication of US3352494A publication Critical patent/US3352494A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • F02K1/085—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone by transversely deforming an internal member
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
    • F02K1/42—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet the means being movable into an inoperative position

Definitions

  • ABSTRACT GF THE DISCLGSURE This invention concerns nozzle.
  • a supersonic jet propulsion nozzle having a substantially cylindrical nozzle casing (or casing assembly) and a bulbous plug mounted therein, the plug and the casing (or casing assembly) being relatively movable axially to permit the throat of the nozzle to be disposed as required either in a position at the downstream end of the casing (01" casing assembly) or in a position upstream of said downstream end, whereby the nozzle may be employed either as a convergent or as a convergent-divergent nozzle, and silencing means for substantially increasing the peripheral area over which the said jet gases mix with the ambient air to substantially reduce the noise created by jet gases passing through the nozzle.
  • the silencing means may accordingly comprise a plurality of angularly spaced apart movable parts which are carried by the plug adjacent the said throat, the said parts being movable into and out of a position in which they prevent jet flow through corresponding portions of the throat.
  • the said movable parts may comprise a plurality of flaps each of which is connected by a linkage to a common actuating member.
  • the actuating member may comprise a sleeve which is axially movable over a tube which is mounted centrally of said plug.
  • a second axially movable sleeve mounted on said tube, the plug being made up of a plurality of pairs of fingers each pair of which comprise fingers mounted on a common pivot connected to the second sleeve for radial movement thereby.
  • the silencing means may comprise a plurality of angularly spaced apart members which are connected to the plug adjacent the said throat, each said member having a downstream portion made up of separable parts which may be moved between a closed position, in which they are closed up against each other, and an open position, in which they are moved apart to permit a flow of ambient air to pass therebetween.
  • each angularly spaced apart member may be an aerofoil-shaped vane having a fixed upstream portion, the downstream portion being made up of two pivoted separable parts.
  • the said separable parts may be arranged to be moved by a mechanical linkage.
  • the casing assembly may have an outer portion which a supersonic jet propulsion 3,352,494 Patented Nov. 1%, 1967 is slidable over an inner portion so as to alter as required the position of the downstream end of the casing assembly.
  • FIGURE 1 is a diagrammatic view of a gas turbine engine provided with a supersonic nozzle according to the present invention
  • FIGURE 2 is a broken away cross sectional view of the supersonic nozzle of the engine of FIGURE 1,
  • FIGURE 3 is a section taken on the line 33 of FIGURE 2,
  • FIGURE 4 is a broken away sectional view of another supersonic nozzle which may be employed in the engine of FIGURE 1,
  • FIGURE 5 is an end view of and FIGURE 6 is a diagrammatic section taken on the line 66 of FIGURE 4.
  • an aircraft Iii is provided with a pod 11 in which is mounted a supersonic gas turbine engine 12.
  • the engine 12 comprises, in flow series, a supersonic intake 13, one or more compressors 14, combustion equipment 15, one or more turbines 16, and a jet pipe 17 which is provided with a thrust reverser (not shown) and with a supersonic nozzle 19.
  • the nozzle 19 has a substantially cylindrical nozzle casing provided with an outer casing portion 22 (FIG. 2) which is slidable over an inner casing portion 23. Within the inner casing portion 23, and spaced therefrom by a throat 24, is a bulbous plug 25.
  • the outer casing portion 22 may be moved (by power means, not shown) between the full line and dotted line positions shown in FIGURE 2. When the outer casing portion 22 is disposed in the full line position, and throat 24 is aligned with the downstream end of the outer casing portion 22, whereby to form the nozzle into a convergent nozzle. When, however, the outer casing portion 22 is moved axially to the dotted line position, the throat 24 will be disposed upstream of the downstream end of the outer casing portion 22, whereby the nozzle will be a convergent/ divergent nozzle.
  • the plug 25 is supported within the inner casing portion 23 by means of a plurality of angularly spaced apart struts 26 each of which is arranged tangentially of the plug 25 so as to help to prevent buckling on difierential expansion and contraction.
  • the plug 25 consists of a substantially conical upstream portion 30 and a conical downstream portion 31, the portions 30, 31 being interconnected by a tube 32 which is mounted central-1y of the plug 25.
  • the central portion of the plug 25 has an outer casing which is made up of a plurality of pairs of fingers 33, 34, Whose ends slightly overlap.
  • the fingers 33, 34 of each said pair are connected by knuckle joints 35, 36 to a common pivot 37 on a link 38, the pivots 37 being disposed adjacent the throat 24.
  • Each of the fingers 33 is mounted at its upstream end on a pivot 39, while each of the fingers 34 is mounted adjacent its downstream end on a pivot 40 carried by a link 41.
  • the various links 38 are connected to a common sleeve 42 which is axially movable, by means of a push rod 43, bet-ween the full line and the dotted line positions shown in FIGURE 2.
  • the push rod 43 is provided with a rack 44 which meshes with a pinion 45, the pinion 45 being mounted on a shaft 46 which extends through one of the struts 26. Power means (not shown) are provided for rotating the shaft 46.
  • the fingers 33, 34 may be disposed either in the full line position shown, or in one of a number of other positions indicated by dotted lines.
  • the outer casing portion 22 may be moved either to form a convergent-divergent nozzle or a convergent nozzle so as to suit the aerodynamic air flow conditions.
  • it may be necessary to alter the area of the throat 24 so as to ensure satisfactory operation of the engine, and the provision of the fingers 33, 34 accordingly enables this to be done.
  • the outer casing portion 22 will be disposed in the full line position, whilst the fingers 33, 34 will be in their outermost position. Just after take-off, however, the fingers 33, 34' are radially retracted so as to permit the throat 24 to have its maximum area.
  • a sleeve 50 which is connected by linkages 51 to a plurality of angularly spaced flaps 52 which are disposed adjacent the throat 24.
  • Each of the flaps 52 is pivoted at 53 in the casing of the central portion of the plug 25.
  • the fiaps 52 are movable between a position, shown-in dotted lines, in which they prevent jet flow through certain parts of the throat 24, and a position, shown in full lines, in which they form part of the casing of the said central portion.
  • the flaps 52 when the flaps 52 are in the dotted line position, they substantially increase the peripheral area over which the jet gases mix with the ambient air. This assists in substantially reducing the noise created by the jet gases passing through the nozzle. Furthermore, when the flaps 52 are in the dotted line position, a depression is formed downstream of them which has the efltect of drawing in ambient air. This promotes mixing of the ambient air with the jet gases and hence promotes still further jet silencing.
  • the fingers 33, 34 may be moved radially inwardly e.g. from the outermost dotted line position to the position of the innermost dotted line.
  • the sleeve 50 is movable between the full line and dotted line positions by means not shown. If desired, the sleeve 50 could be moved axially by means connected to the push rod 43, or to an additional separately actuated push rod (not shown).
  • FIGURES 4-6 there is shown a modified supersonic nozzle which may be used on the engine 12.
  • the said nozzle has a a substantially cylindrical nozzle casing provided with an outer casing portion 100 which is slidable over an inner casing portion 101.
  • a bulbous plug 103 Within the inner casing portion 101, and spaced therefrom by a throat 102, is a bulbous plug 103.
  • the outer casing portion 100 may be moved by a pneumatically operated ram 104 between the full line and dotted line positions shown in FIGURE 4. -When the outer casing portion 100 is disposed in the full line position, the throat 102 is aligned with the downstream end of the outer casing portion 100, whereby to form the nozzle into a convergent nozzle. When, however, the outer casing portion 100 is moved axially by the ram 104 to the dotted line position, the throat 102 will be disposed upstream of the downstream end of the outer casing portion 100, whereby the nozzle will be a convergent-divergent nozzle.
  • the plug 103 is supported within the inner casing portion 101. by means of a plurality of angularly spaced apart aerofoil-shaped struts 105, 106 each of which is arranged tangentially of the plug 103.
  • the plug 103 is also provided with a plurality of angularly spaced apart aerofoil-shaped vanes 107 which are connected to the plug 103 adjacent the throat 102.
  • the struts 105 and vanes 107 are respectively provided with rollers 110, 111 for engagement by the outer casing portion 100.
  • the plug 103 has an outer casing 112 in which are mounted a plurality of angularly spaced apart aerofoilshaped members 113 each of which is mounted at the d, downstream end of an arm 114 whose upstream end is pivoted at 115.
  • Each of the members 113 is radially movable between an inoperative position in which it lies within the confines of the outer casing 112 and an operative position (indicated in full lines) in which it extends outwardly thereof.
  • Each of the members 113 is connected by a link 116 to a sleeve 117.
  • the sleeve 117 is slidable over an axially extending tube 120 which is disposed within the plug 103.
  • the upstream end of the tube 120 is supported by the struts 106, while the downstream end of the tube 120 is supported from the outer casing 112 by a casing 122.
  • a pneumatically actuated ram 123 is arranged to move the sleeve 117, and hence the members 113, by way of a mechanical linkage comprising a bell crank lever 124, a link 125 passing through a strut 105, a bell crank lever 126, and a link 127.
  • the members 113 may thus be moved by the ram 123 so as to adjust the area of flow through the throat 102 both when the nozzle is in its convergent and when it is in its convergent-divergent position.
  • the outer casing portion 100 may he moved by the ram 104 either to form a convergent-divergent nozzle or a convergent nozzle so as to suit the aerodynamic air flow conditions.
  • the members 113 are, moreover, moved by a mechanical linkage renders the construction particularly suitable for the high temperatures which will be experienced in operation.
  • Each of the vanes 107 has a fixed upstream portion 131 (see FIG. 6) and a downstream portion which is made up of two pivoted separable parts 132, 133.
  • the parts 132, 133 are connected to a common push rod 134 by links 135, 136 respectively.
  • the push rod 134 the parts 132, 133 may be moved between a closed position (shown in full lines) in which they are closed up against each other, and an open position (shown in dotted lines) in which they are disposed apart to permit a flow of ambient air therebetween.
  • the parts 132, 133 are, therefore, in their open position, a flow of air will be drawn between them and will reduce the noise created by the jet gases passing through the nozzle, by virtue of increasing the peripheral area over which the jet gases mix with the ambient air.
  • each vane 107 is connected by a bell crank lever 140 and link 141 to a bell crank lever 142.
  • the latter is mounted on a fixed sleeve 143 secured on the tube 120.
  • the bell crank lever 142 is connected by a link 144 to a sleeve 145 which is slidable along the tube 120.
  • the sleeve 145 is provided with a diametrically extending plate 146 which passes through a slot in the tube 120.
  • the plate 146 is connected to a pneumatically operated ram 147 by way of a mechanical linkage comprising a bell crank lever 150, a link 151 extending through a strut 105, a bell crank lever 152 and a link 153.
  • a supersonic jet propulsion nozzle having a substantially cylindrical nozzle casing and a bulbous plug mounted therein, the plug and the casing being relatively movable axially to permit the throat of the nozzle to be disposed as required either in a position at the downstream end of the casing or in a position upstream of said downstream end, whereby the nozzle may be employed either as a convergent or as a convergent-divergent nozzle, and a plurality of angularly spaced apart aerofoil shaped vanes which are connected to the plug adjacent the said throat, each said member having a fixed upstream portion and a downstream portion made up of two pivoted separable parts which may be moved between a closed position, in which they are closed up against each other, and an open position, in which they are moved apart to permit a How of ambient air to pass therebetween thereby substantially increasing the peripheral area over which the said jet gases mix with the ambient air to substantially reduce the noise created by jet gases passing through the nozzle.
  • a supersonic jet propulsion nozzle comprising: a substantially cylindrical nozzle casing having a downstream end; a bulbous plug mounted in said casing and defining with said casing a throat; said plug and said casing being movable axially relative to each other as desired between at least two positions, one position in which said throat is at the downstream end of said casing and defines a convergent nozzle and the other position in which said throat is upstream of said downstream end of said casing and defines a convergent-divergent.nozzle; transversely movable portions on said plug for varying the area of said throat in each of said one and said other positions of said plug relative to said casing; and silencing means, independent of and angularly spaced relative to said movable portions, for substantially increasing peripheral area over which jet gases mix with ambient air to substantially reduce the noise created by jet gases passing through said nozzle.
  • a supersonic jet propulsion nozzle as claimed in claim 2 in which said silencing means comprise a plurality of angularly spaced apart movable parts carried by said plug adjacent said throat, said movable parts being movable into and out of a position in which said parts prevent jet flow through corresponding portions of said throat.
  • a supersonic jet propulsion nozzle as claimed in claim 2 in which said silencing means comprise a plurality of angularly spaced apart movable flaps carried by the plug adjacent said throat, a common actuating member and a linkage connecting each flap to said actuating member for movement into and out of a position in which said flaps prevent jet flow through corresponding portions of the throat.
  • a supersonic jet propulsion nozzle as claimed in claim 2 in which said substantially cylindrical nozzle casing comprises a fixed inner portion and a movable outer portion, said outer portion being movable axially relative to the bulbous plug to permit the throat of the nozzle to be disposed as required in either of said positions.
  • a supersonic jet propulsion nozzle comprising: a substantially cylindrical nozzle casing having a downstream end; a bulbous plug mounted in said casing and defining with said casing a throat; said plug and said casing being movable axially relative to each other as desired between at least two positions, one position in which said throat is at the downstream end of said casing and defines a convergent nozzle and the other position in which said throat is upstream of said downstream end of said casing and defines a convergentdivergent nozzle; movable portions on said plug for varying the area of said throat in each of said one and said other positions of said plug relative to said casing; and silencing means, independent of said movable portions, for substantially increasing peripheral area over which jet gases mix with ambient air to substantially reduce the noise created by jet gases passing through said nozzle, said silencing means including a plurality of angularly spaced apart fixed members connected to said plug adjacent said throat, said fixed members extending radially across said throat, and each of said members having a downstream

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Special Spraying Apparatus (AREA)

Description

F. J. COLVILLE- ET AL 3,352,494 SUPERSONIC JET PROPULSION NOZZLE Nov. 14, 1967 5 Sheets-Sheet 1 Filed July 26, 1965 l ento r ttorney NOV. 14, 1967 co v g ET AL 3,352,494
SUPERSONIC JET PROPULSION NOZZLE Nov. 14, 1967 F. J. COLVILLE ET AL 3,352,494
SUPERSONIC JET PROPULSION NOZZLE Filed July 26, 1965 5 Sheets-Sheet 3 United States Patent Ofilice 3,352,494 SUPERSONIC EET PROPULSION NOZZLE Francis Jetfrey Colville, Sutton-in-Ashfield, Norman Roberts, Huclrnell, and David Morris Brown, Allestree, Derby, England, assignors to Rolls-Royce Limited, Derby, England, a British company Filed July 26, 1965, Ser. No.
474,795 Claims priority,
application Great Britain, Aug. 25, 1964,
34,817/64 6 Claims. (Cl. 239-26513) ABSTRACT GF THE DISCLGSURE This invention concerns nozzle.
According to the present invention, there is provided a supersonic jet propulsion nozzle having a substantially cylindrical nozzle casing (or casing assembly) and a bulbous plug mounted therein, the plug and the casing (or casing assembly) being relatively movable axially to permit the throat of the nozzle to be disposed as required either in a position at the downstream end of the casing (01" casing assembly) or in a position upstream of said downstream end, whereby the nozzle may be employed either as a convergent or as a convergent-divergent nozzle, and silencing means for substantially increasing the peripheral area over which the said jet gases mix with the ambient air to substantially reduce the noise created by jet gases passing through the nozzle.
The silencing means may accordingly comprise a plurality of angularly spaced apart movable parts which are carried by the plug adjacent the said throat, the said parts being movable into and out of a position in which they prevent jet flow through corresponding portions of the throat. V
The said movable parts may comprise a plurality of flaps each of which is connected by a linkage to a common actuating member. Thus the actuating member may comprise a sleeve which is axially movable over a tube which is mounted centrally of said plug.
There may be a second axially movable sleeve mounted on said tube, the plug being made up of a plurality of pairs of fingers each pair of which comprise fingers mounted on a common pivot connected to the second sleeve for radial movement thereby.
Alternatively, the silencing means may comprise a plurality of angularly spaced apart members which are connected to the plug adjacent the said throat, each said member having a downstream portion made up of separable parts which may be moved between a closed position, in which they are closed up against each other, and an open position, in which they are moved apart to permit a flow of ambient air to pass therebetween.
Thus each angularly spaced apart member may be an aerofoil-shaped vane having a fixed upstream portion, the downstream portion being made up of two pivoted separable parts. The said separable parts may be arranged to be moved by a mechanical linkage.
The casing assembly may have an outer portion which a supersonic jet propulsion 3,352,494 Patented Nov. 1%, 1967 is slidable over an inner portion so as to alter as required the position of the downstream end of the casing assembly.
The invention is illustrated, merely by way of example, in the accompanying drawings, in which:
FIGURE 1 is a diagrammatic view of a gas turbine engine provided with a supersonic nozzle according to the present invention,
FIGURE 2 is a broken away cross sectional view of the supersonic nozzle of the engine of FIGURE 1,
FIGURE 3 is a section taken on the line 33 of FIGURE 2,
FIGURE 4 is a broken away sectional view of another supersonic nozzle which may be employed in the engine of FIGURE 1,
FIGURE 5 is an end view of and FIGURE 6 is a diagrammatic section taken on the line 66 of FIGURE 4.
Referring first to FIGURE 1, an aircraft Iii is provided with a pod 11 in which is mounted a supersonic gas turbine engine 12. The engine 12 comprises, in flow series, a supersonic intake 13, one or more compressors 14, combustion equipment 15, one or more turbines 16, and a jet pipe 17 which is provided with a thrust reverser (not shown) and with a supersonic nozzle 19.
The nozzle 19 has a substantially cylindrical nozzle casing provided with an outer casing portion 22 (FIG. 2) which is slidable over an inner casing portion 23. Within the inner casing portion 23, and spaced therefrom by a throat 24, is a bulbous plug 25. The outer casing portion 22 may be moved (by power means, not shown) between the full line and dotted line positions shown in FIGURE 2. When the outer casing portion 22 is disposed in the full line position, and throat 24 is aligned with the downstream end of the outer casing portion 22, whereby to form the nozzle into a convergent nozzle. When, however, the outer casing portion 22 is moved axially to the dotted line position, the throat 24 will be disposed upstream of the downstream end of the outer casing portion 22, whereby the nozzle will be a convergent/ divergent nozzle.
The plug 25 is supported within the inner casing portion 23 by means of a plurality of angularly spaced apart struts 26 each of which is arranged tangentially of the plug 25 so as to help to prevent buckling on difierential expansion and contraction.
The plug 25 consists of a substantially conical upstream portion 30 and a conical downstream portion 31, the portions 30, 31 being interconnected by a tube 32 which is mounted central-1y of the plug 25.
The central portion of the plug 25 has an outer casing which is made up of a plurality of pairs of fingers 33, 34, Whose ends slightly overlap. The fingers 33, 34 of each said pair are connected by knuckle joints 35, 36 to a common pivot 37 on a link 38, the pivots 37 being disposed adjacent the throat 24. Each of the fingers 33 is mounted at its upstream end on a pivot 39, while each of the fingers 34 is mounted adjacent its downstream end on a pivot 40 carried by a link 41.
The various links 38 are connected to a common sleeve 42 which is axially movable, by means of a push rod 43, bet-ween the full line and the dotted line positions shown in FIGURE 2. The push rod 43 is provided with a rack 44 which meshes with a pinion 45, the pinion 45 being mounted on a shaft 46 which extends through one of the struts 26. Power means (not shown) are provided for rotating the shaft 46.
Accordingly, by appropriate movement of the push rod 43, the fingers 33, 34 may be disposed either in the full line position shown, or in one of a number of other positions indicated by dotted lines. Thus, as will be appreciated, the ability to move the fingers 33, 34 radially, and
the nozzle of FIGURE 4,
thus to adjust the peripheral shape of the central portion of the plug 25, enables the area of fiow'through the throat 24 to be adjusted both when the outer casing portion 22 is in the full line and when it is in the dotted line position.
Thus the outer casing portion 22 may be moved either to form a convergent-divergent nozzle or a convergent nozzle so as to suit the aerodynamic air flow conditions. However, for high Mach numbers, it may be necessary to alter the area of the throat 24 so as to ensure satisfactory operation of the engine, and the provision of the fingers 33, 34 accordingly enables this to be done.
Thus, for example, at take-oil, the outer casing portion 22 will be disposed in the full line position, whilst the fingers 33, 34 will be in their outermost position. Just after take-off, however, the fingers 33, 34' are radially retracted so as to permit the throat 24 to have its maximum area.
Slidably mounted on the tube 32 is a sleeve 50 which is connected by linkages 51 to a plurality of angularly spaced flaps 52 which are disposed adjacent the throat 24. Each of the flaps 52 is pivoted at 53 in the casing of the central portion of the plug 25. The fiaps 52 are movable between a position, shown-in dotted lines, in which they prevent jet flow through certain parts of the throat 24, and a position, shown in full lines, in which they form part of the casing of the said central portion.
It will be appreciated that when the flaps 52 are in the dotted line position, they substantially increase the peripheral area over which the jet gases mix with the ambient air. This assists in substantially reducing the noise created by the jet gases passing through the nozzle. Furthermore, when the flaps 52 are in the dotted line position, a depression is formed downstream of them which has the efltect of drawing in ambient air. This promotes mixing of the ambient air with the jet gases and hence promotes still further jet silencing.
In order to compensate for the reduction in the effective area of the throat 24 when the flaps 52 are in the dotted line position, the fingers 33, 34 may be moved radially inwardly e.g. from the outermost dotted line position to the position of the innermost dotted line.
The sleeve 50 is movable between the full line and dotted line positions by means not shown. If desired, the sleeve 50 could be moved axially by means connected to the push rod 43, or to an additional separately actuated push rod (not shown).
In FIGURES 4-6 there is shown a modified supersonic nozzle which may be used on the engine 12. The said nozzle has a a substantially cylindrical nozzle casing provided with an outer casing portion 100 which is slidable over an inner casing portion 101.
Within the inner casing portion 101, and spaced therefrom by a throat 102, is a bulbous plug 103. The outer casing portion 100 may be moved by a pneumatically operated ram 104 between the full line and dotted line positions shown in FIGURE 4. -When the outer casing portion 100 is disposed in the full line position, the throat 102 is aligned with the downstream end of the outer casing portion 100, whereby to form the nozzle into a convergent nozzle. When, however, the outer casing portion 100 is moved axially by the ram 104 to the dotted line position, the throat 102 will be disposed upstream of the downstream end of the outer casing portion 100, whereby the nozzle will be a convergent-divergent nozzle.
The plug 103 is supported within the inner casing portion 101. by means of a plurality of angularly spaced apart aerofoil-shaped struts 105, 106 each of which is arranged tangentially of the plug 103. The plug 103 is also provided with a plurality of angularly spaced apart aerofoil-shaped vanes 107 which are connected to the plug 103 adjacent the throat 102. The struts 105 and vanes 107 are respectively provided with rollers 110, 111 for engagement by the outer casing portion 100.
The plug 103 has an outer casing 112 in which are mounted a plurality of angularly spaced apart aerofoilshaped members 113 each of which is mounted at the d, downstream end of an arm 114 whose upstream end is pivoted at 115.
Each of the members 113 is radially movable between an inoperative position in which it lies within the confines of the outer casing 112 and an operative position (indicated in full lines) in which it extends outwardly thereof.
Each of the members 113 is connected by a link 116 to a sleeve 117. The sleeve 117 is slidable over an axially extending tube 120 which is disposed within the plug 103. The upstream end of the tube 120 is supported by the struts 106, while the downstream end of the tube 120 is supported from the outer casing 112 by a casing 122.
A pneumatically actuated ram 123 is arranged to move the sleeve 117, and hence the members 113, by way of a mechanical linkage comprising a bell crank lever 124, a link 125 passing through a strut 105, a bell crank lever 126, and a link 127.
The members 113 may thus be moved by the ram 123 so as to adjust the area of flow through the throat 102 both when the nozzle is in its convergent and when it is in its convergent-divergent position. Thus the outer casing portion 100 may he moved by the ram 104 either to form a convergent-divergent nozzle or a convergent nozzle so as to suit the aerodynamic air flow conditions. However, for high Mach numbers it may be necessary to alter the area of the throat 102 so as to ensure satisfactory operation of the engine, and the provision of the members 113 enables this to be done. The fact that the members 113 are, moreover, moved by a mechanical linkage renders the construction particularly suitable for the high temperatures which will be experienced in operation.
Each of the vanes 107 has a fixed upstream portion 131 (see FIG. 6) and a downstream portion which is made up of two pivoted separable parts 132, 133. The parts 132, 133 are connected to a common push rod 134 by links 135, 136 respectively. Thus by movement of the push rod 134 the parts 132, 133 may be moved between a closed position (shown in full lines) in which they are closed up against each other, and an open position (shown in dotted lines) in which they are disposed apart to permit a flow of ambient air therebetween. When the parts 132, 133 are, therefore, in their open position, a flow of air will be drawn between them and will reduce the noise created by the jet gases passing through the nozzle, by virtue of increasing the peripheral area over which the jet gases mix with the ambient air.
The push rod 134 of each vane 107 is connected by a bell crank lever 140 and link 141 to a bell crank lever 142.
The latter is mounted on a fixed sleeve 143 secured on the tube 120.
The bell crank lever 142 is connected by a link 144 to a sleeve 145 which is slidable along the tube 120. The sleeve 145 is provided with a diametrically extending plate 146 which passes through a slot in the tube 120. The plate 146 is connected to a pneumatically operated ram 147 by way of a mechanical linkage comprising a bell crank lever 150, a link 151 extending through a strut 105, a bell crank lever 152 and a link 153.
We claim:
1. A supersonic jet propulsion nozzle having a substantially cylindrical nozzle casing and a bulbous plug mounted therein, the plug and the casing being relatively movable axially to permit the throat of the nozzle to be disposed as required either in a position at the downstream end of the casing or in a position upstream of said downstream end, whereby the nozzle may be employed either as a convergent or as a convergent-divergent nozzle, and a plurality of angularly spaced apart aerofoil shaped vanes which are connected to the plug adjacent the said throat, each said member having a fixed upstream portion and a downstream portion made up of two pivoted separable parts which may be moved between a closed position, in which they are closed up against each other, and an open position, in which they are moved apart to permit a How of ambient air to pass therebetween thereby substantially increasing the peripheral area over which the said jet gases mix with the ambient air to substantially reduce the noise created by jet gases passing through the nozzle.
2. A supersonic jet propulsion nozzle comprising: a substantially cylindrical nozzle casing having a downstream end; a bulbous plug mounted in said casing and defining with said casing a throat; said plug and said casing being movable axially relative to each other as desired between at least two positions, one position in which said throat is at the downstream end of said casing and defines a convergent nozzle and the other position in which said throat is upstream of said downstream end of said casing and defines a convergent-divergent.nozzle; transversely movable portions on said plug for varying the area of said throat in each of said one and said other positions of said plug relative to said casing; and silencing means, independent of and angularly spaced relative to said movable portions, for substantially increasing peripheral area over which jet gases mix with ambient air to substantially reduce the noise created by jet gases passing through said nozzle.
3. A supersonic jet propulsion nozzle as claimed in claim 2 in which said silencing means comprise a plurality of angularly spaced apart movable parts carried by said plug adjacent said throat, said movable parts being movable into and out of a position in which said parts prevent jet flow through corresponding portions of said throat.
4. A supersonic jet propulsion nozzle as claimed in claim 2 in which said silencing means comprise a plurality of angularly spaced apart movable flaps carried by the plug adjacent said throat, a common actuating member and a linkage connecting each flap to said actuating member for movement into and out of a position in which said flaps prevent jet flow through corresponding portions of the throat.
5. A supersonic jet propulsion nozzle as claimed in claim 2 in which said substantially cylindrical nozzle casing comprises a fixed inner portion and a movable outer portion, said outer portion being movable axially relative to the bulbous plug to permit the throat of the nozzle to be disposed as required in either of said positions.
6. A supersonic jet propulsion nozzle comprising: a substantially cylindrical nozzle casing having a downstream end; a bulbous plug mounted in said casing and defining with said casing a throat; said plug and said casing being movable axially relative to each other as desired between at least two positions, one position in which said throat is at the downstream end of said casing and defines a convergent nozzle and the other position in which said throat is upstream of said downstream end of said casing and defines a convergentdivergent nozzle; movable portions on said plug for varying the area of said throat in each of said one and said other positions of said plug relative to said casing; and silencing means, independent of said movable portions, for substantially increasing peripheral area over which jet gases mix with ambient air to substantially reduce the noise created by jet gases passing through said nozzle, said silencing means including a plurality of angularly spaced apart fixed members connected to said plug adjacent said throat, said fixed members extending radially across said throat, and each of said members having a downstream portion made up of separable parts which are movable between a closed position, in which the separable parts are closed up against each other, and an open position, in which the separable parts are moved apart to permit a flow of ambient air to pass therebetween thereby substantially increasing peripheral area over which jet gases mix with the ambient air.
References Cited UNITED STATES PATENTS 2,570,629 10/1951 Anxionnaz 239-26533 2,938,335 5/1960 Cook 239265.13
FOREIGN PATENTS 950,288 2/1964 Great Britain.
EVERETT W. KIRBY, Primary Examiner.

Claims (1)

  1. 2. A SUPERSONIC JET PROPULSION NOZZLE COMPRISING: A SUBSTANTIALLY CYLINDRICAL NOZZLE CASING HAVING A DOWNSTREAM END; A BULBOUS PLUG MOUNTED IN SAID CASING AND DEFINING WITH SAID CASING A THROAT; SAID PLUG AND SAID CASING BEING MOVABLE AXIALLY RELATIVE TO EACH OTHER AS DESIRED BETWEEN AT LEAST TWO POSITIONS, ONE POSITION IN WHICH SAID THROAT IS AT THE DOWNSTREAM END OF SAID CASING AND DEFINES A CONVERGENT NOZZLE AND THE OTHER POSITION IN WHICH SAID THROAT IS UPSTREAM OF SAID DOWNSTREAM END OF SAID CASING AND DEFINES A CONVERGENT-DIVERGENT NOZZLE; TRANVERSELY MOVABLE PORTIONS ON SAID PLUG FOR VARYING THE AREA OF SAID THROAT IN EACH OF SAID ONE AND SAID OTHER POSITIONS OF SAID PLUG RELATIVE TO SAID CASING; AND SILENCING MEANS, INDEPENDENT OF AND ANGULARLY SPACED RELATIVE TO SAID MOVABLE PORTIONS, FOR SUBSTANTIALLY INCREASING PERIPHERAL AREA OVER WHICH JET GASES MIX WITH AMBIENT AIR TO SUBSTANTIALLY REDUCE THE NOISE CREATED BY JET GASES PASSING THROUGH SAID NOZZLE.
US474795A 1964-08-25 1965-07-26 Supersonic jet propulsion nozzle Expired - Lifetime US3352494A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB34817/64A GB1009776A (en) 1964-08-25 1964-08-25 Supersonic jet propulsion nozzle

Publications (1)

Publication Number Publication Date
US3352494A true US3352494A (en) 1967-11-14

Family

ID=10370275

Family Applications (1)

Application Number Title Priority Date Filing Date
US474795A Expired - Lifetime US3352494A (en) 1964-08-25 1965-07-26 Supersonic jet propulsion nozzle

Country Status (3)

Country Link
US (1) US3352494A (en)
DE (1) DE1286334B (en)
GB (2) GB1009776A (en)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3598318A (en) * 1970-04-10 1971-08-10 Boeing Co Movable acoustic splitter for nozzle area control and thrust reversal
US3774868A (en) * 1972-12-11 1973-11-27 G Goetz Integrated nozzle
US3814324A (en) * 1972-06-19 1974-06-04 Gen Electric Propulsion nozzle and actuator system employed therein
US4039146A (en) * 1975-12-01 1977-08-02 General Electric Company Variable cycle plug nozzle and flap and method of operating same
US4043508A (en) * 1975-12-01 1977-08-23 General Electric Company Articulated plug nozzle
US4074859A (en) * 1976-11-10 1978-02-21 The United States Of America As Represented By The Secretary Of The Air Force Deformable plug for an aircraft engine exhaust nozzle
US4088270A (en) * 1976-03-31 1978-05-09 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Two dimensional wedge/translating shroud nozzle
US4196856A (en) * 1977-11-25 1980-04-08 The Boeing Company Variable geometry convergent divergent exhaust nozzle
US4537026A (en) * 1982-04-07 1985-08-27 Rolls-Royce Inc. Variable area nozzles for turbomachines
US5463866A (en) * 1993-12-30 1995-11-07 The Boeing Company Supersonic jet engine installation and method with sound suppressing nozzle
US5884843A (en) * 1996-11-04 1999-03-23 The Boeing Company Engine noise suppression ejector nozzle
US5908159A (en) * 1997-02-24 1999-06-01 The Boeing Company Aircraft chute ejector nozzle
US5941065A (en) * 1996-11-04 1999-08-24 The Boeing Company Stowable mixer ejection nozzle
US5970705A (en) * 1979-08-17 1999-10-26 Rolls Royce, Limited Variable configuration final nozzle assembly for a combined rocket/ramjet engine
US20080112801A1 (en) * 2006-11-14 2008-05-15 Thomas Ory Moniz Turbofan engine cowl assembly and method of operating the same
US20160003190A1 (en) * 2014-06-09 2016-01-07 United Technologies Corporation Variable area nozzle for gas turbine engine
CN114127406A (en) * 2019-06-06 2022-03-01 赛峰飞机发动机公司 Confluence structure of main flow and secondary flow in two-way turbine engine
US11274631B2 (en) 2020-02-27 2022-03-15 Rolls-Royce North American Technologies Inc. Methodology for minimizing aerodynamic buzz in an exhaust nozzle
US11313320B2 (en) * 2020-02-27 2022-04-26 Rolls-Royce North American Technologies Inc. Exhaust nozzle with centerbody support structure for a gas turbine engine
US11319832B2 (en) 2020-02-27 2022-05-03 Rolls-Royce North American Technologies Inc. Single movement convergent and convergent-divergent nozzle

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5261229A (en) * 1992-08-03 1993-11-16 General Electric Company Noise-suppressed exhaust nozzles for jet engines
USD1015134S1 (en) * 2022-02-21 2024-02-20 Jason D. Kerlin Spool head thumb screw

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2570629A (en) * 1945-10-05 1951-10-09 Anxionnaz Adjustable pipe for the intake of air and expansion of the driving gases in reactionjet propellers for projectiles and vehicles
US2938335A (en) * 1958-04-14 1960-05-31 Boeing Co Noise suppressor and thrust reverser
GB950288A (en) * 1959-08-18 1964-02-26 Bristol Siddeley Engines Ltd Improvements in nozzles for aircraft propulsion

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB677973A (en) * 1951-02-22 1952-08-27 Blackburn & Gen Aircraft Ltd Improvements in and relating to variable area nozzles for turbo-jet engine installations
US2788635A (en) * 1953-10-22 1957-04-16 North American Aviation Inc Device for varying a jet engine orifice
BE537645A (en) * 1954-06-10
US2940252A (en) * 1956-02-07 1960-06-14 Boeing Co Gas stream thrust reaction propulsion engines with noise-suppression and thrust-reversing nozzle means
US2845775A (en) * 1956-06-01 1958-08-05 United Aircraft Corp Noise suppressors for jet engines
US3055174A (en) * 1957-01-14 1962-09-25 Boeing Co Retractable noise suppressor for jet engines
GB920889A (en) * 1960-11-14 1963-03-13 Rolls Royce Improvements relating to the silencing of gas turbine engines

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2570629A (en) * 1945-10-05 1951-10-09 Anxionnaz Adjustable pipe for the intake of air and expansion of the driving gases in reactionjet propellers for projectiles and vehicles
US2938335A (en) * 1958-04-14 1960-05-31 Boeing Co Noise suppressor and thrust reverser
GB950288A (en) * 1959-08-18 1964-02-26 Bristol Siddeley Engines Ltd Improvements in nozzles for aircraft propulsion

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3598318A (en) * 1970-04-10 1971-08-10 Boeing Co Movable acoustic splitter for nozzle area control and thrust reversal
US3814324A (en) * 1972-06-19 1974-06-04 Gen Electric Propulsion nozzle and actuator system employed therein
US3774868A (en) * 1972-12-11 1973-11-27 G Goetz Integrated nozzle
US4039146A (en) * 1975-12-01 1977-08-02 General Electric Company Variable cycle plug nozzle and flap and method of operating same
US4043508A (en) * 1975-12-01 1977-08-23 General Electric Company Articulated plug nozzle
US4088270A (en) * 1976-03-31 1978-05-09 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Two dimensional wedge/translating shroud nozzle
US4074859A (en) * 1976-11-10 1978-02-21 The United States Of America As Represented By The Secretary Of The Air Force Deformable plug for an aircraft engine exhaust nozzle
US4196856A (en) * 1977-11-25 1980-04-08 The Boeing Company Variable geometry convergent divergent exhaust nozzle
US5970705A (en) * 1979-08-17 1999-10-26 Rolls Royce, Limited Variable configuration final nozzle assembly for a combined rocket/ramjet engine
US4537026A (en) * 1982-04-07 1985-08-27 Rolls-Royce Inc. Variable area nozzles for turbomachines
US5463866A (en) * 1993-12-30 1995-11-07 The Boeing Company Supersonic jet engine installation and method with sound suppressing nozzle
US5941065A (en) * 1996-11-04 1999-08-24 The Boeing Company Stowable mixer ejection nozzle
US5884843A (en) * 1996-11-04 1999-03-23 The Boeing Company Engine noise suppression ejector nozzle
US5908159A (en) * 1997-02-24 1999-06-01 The Boeing Company Aircraft chute ejector nozzle
US20080112801A1 (en) * 2006-11-14 2008-05-15 Thomas Ory Moniz Turbofan engine cowl assembly and method of operating the same
US7886518B2 (en) * 2006-11-14 2011-02-15 General Electric Company Turbofan engine cowl assembly and method of operating the same
US20110120136A1 (en) * 2006-11-14 2011-05-26 Thomas Ory Moniz Method of operating a turbofan engine cowl assembly
US8091334B2 (en) 2006-11-14 2012-01-10 General Electric Company Method of operating a turbofan engine cowl assembly
US20160003190A1 (en) * 2014-06-09 2016-01-07 United Technologies Corporation Variable area nozzle for gas turbine engine
US9828943B2 (en) * 2014-06-09 2017-11-28 United Technologies Corporation Variable area nozzle for gas turbine engine
CN114127406A (en) * 2019-06-06 2022-03-01 赛峰飞机发动机公司 Confluence structure of main flow and secondary flow in two-way turbine engine
CN114127406B (en) * 2019-06-06 2024-05-10 赛峰飞机发动机公司 Convergence structure of main flow and secondary flow in two-way turbine engine
US11274631B2 (en) 2020-02-27 2022-03-15 Rolls-Royce North American Technologies Inc. Methodology for minimizing aerodynamic buzz in an exhaust nozzle
US11313320B2 (en) * 2020-02-27 2022-04-26 Rolls-Royce North American Technologies Inc. Exhaust nozzle with centerbody support structure for a gas turbine engine
US11319832B2 (en) 2020-02-27 2022-05-03 Rolls-Royce North American Technologies Inc. Single movement convergent and convergent-divergent nozzle
US11680495B2 (en) 2020-02-27 2023-06-20 Rolls-Royce North American Technologies Inc. Single movement convergent and convergent-divergent nozzle

Also Published As

Publication number Publication date
DE1286334B (en) 1969-01-02
GB1009777A (en) 1965-11-10
GB1009776A (en) 1965-11-10

Similar Documents

Publication Publication Date Title
US3352494A (en) Supersonic jet propulsion nozzle
US2770944A (en) Variable area reaction nozzle movable from convergent to convergent-di-vergent form
US3262268A (en) Thrust reverser
US3483702A (en) Fan thrust reverser for a jet propulsion plant
US4716724A (en) Gas turbine engine powerplant with flow control devices
US3524588A (en) Silencer for aircraft jet engines
US3409228A (en) Ejector nozzle
US2984068A (en) Propulsive nozzle system for reaction propulsion units
US4052847A (en) Gas turbine engine gas flow ducts
US3807637A (en) Variable-geometry convergent-divergent nozzles for jet propulsion engines
US3172256A (en) Jet engine thrust reversers
US3367579A (en) Supersonic convergent-divergent jet exhaust nozzle
GB2308866A (en) Ducted fan gas turbine engine with secondary duct
US3386658A (en) Convergent-divergent jet exhaust nozzle for supersonic aircraft
GB1293868A (en) An arrangement for controlling and supporting a variable-geometry duct
GB2145160A (en) Variable cycle gas turbine engine
US3262269A (en) Thrust reverser
US3062003A (en) Variable area exhaust nozzle
US2972860A (en) Combined variable ejector and thrust reverser
US4502636A (en) Variable geometry ejector nozzle for turbomachines
GB750307A (en) Improvements relating to variable nozzles for gas-turbine jet propulsion engines
US3780827A (en) Gas turbine exhaust nozzle
US3261164A (en) Convergent-divergent co-annular primary nozzle
US4502638A (en) Turbomachine ejector nozzle and thrust reverser
US3568794A (en) Method and apparatus for suppressing the noise of a fan-jet engine