US2529958A - Means for supporting gas-turbine power plants - Google Patents

Means for supporting gas-turbine power plants Download PDF

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US2529958A
US2529958A US709522A US70952246A US2529958A US 2529958 A US2529958 A US 2529958A US 709522 A US709522 A US 709522A US 70952246 A US70952246 A US 70952246A US 2529958 A US2529958 A US 2529958A
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compressor
turbine
plant
power
casing
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US709522A
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Owner Frank Morgan
Henstridge Alec George
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Bristol Aeroplane Co Ltd
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Bristol Aeroplane Co Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type 

Definitions

  • This invention concerns means for supporting a gas-turbine power-plant.
  • the object of this invention is to provide a support which enables the external loads of one or more members of the power-plant to be borne solely by said member or members.
  • the external loads that is, those due to weight and inertia forces
  • means for supporting a gas-turbine power-plant is attached to the power-plant atpositions spaced along the length thereof, part of the plant being supported cantileverwise of said means and part between said-attachments.
  • the present invention find particular appl cation to gas-turbine power plants having an ax1alflow compressor and, according to another feature of the present invention, such a power-plant is supported as described with said compressor disposed between said attachments. As a consequence the compressor is relieved of the external loads due to the other parts of the power-plant.
  • Thesta-tor casing may be designed, therefore, to carry the-loads due to the operation of the compressor and only the external loads of the compressor.
  • that part of the power-plant which is disposed between the attachments is capable of g a limited movement relatively to the supporting structure in an axial and/or radial direction of the power-plant.
  • Figure 1 is a side elevation of a gas-turbine power-plant'having support means in accordance with the invention.
  • Figure 2 is a section on the line 2-2 of Figure 1 and 4 Figure 3 is a section on the line 33 of Figure 1 but to an enlarged scale.
  • the gas-turbine power-plant which is about to be described is adapted for the propulsion of an aeroplane and comprises a compressor unit generally indicated by the reference numeral 5, a turbine 6 for driving the compressor unit, a plurality of combustion chambers land a tail pipe 8.
  • the turbine 6 is disposed adjacent the tail pipe 8 (being at the rear end of the power-plant) and is connected with an axial and centrifugal compressor 9 and Ill respectively;
  • the axial and centrifugal compressors together constitute the comw 690, August 8, 1946 October 9, 1965 3 Claims. (Cl. 604l) pressor unit 5.
  • the compressors are disposed in line with the turbine 6 and between the latter and a housing II
  • the latter carries a group of power plant ancillaries such as at [2, I 3, l4 and I5. It is clear from Figure 1 that these are disposed at the opposite end of the power-plant to the turbine 6, that is, at the front end of the power-plant.
  • the working fluid is admitted to the axial compressor between the latter and the turbine l as at l6 and thereafter the working fluid passes in succession through the axial compressor 9 and the centrifugal compressor III, which is of the two-stage type.
  • the working fluid (during compression) therefore travels from the rear end of the power-plant to the front end where it is discharged into the combustion chambers 1.
  • the latter are spaced around the compressor 9 and convey the working fluid rearwardly from the centrifugal compressor III to the turbine 6.
  • the output shaft of the turbine 6 passes through the turbine casing and is suitably connected with a shaft (not shown) which supports the rotor and impellers of the compressor unit which extends into the housing II. In this way drive is transmitted from the turbine to the compressor unit and also to the ancillaries.
  • the various members of. the power-plant are subjected to loads due to their operation and also to external loads due to the weight of the powerplant and as a result of the aeroplane being manoeuvred. It is desirable that the stator casing of compressor 9 be relieved of these external loads, the casing being required to carry only those loads due to the operation of the compressor and the external loads to which this stator casing alone is subjected.
  • That end of the stator casing which in part defines the mouth I! of the compressor 9 is attached to an annular member I8 which is itself supported from a structure IS.
  • the delivery end of the stator casing is secured to the casing of the centrifugal compressor In as at 20.
  • the casing of the centrifugal compressor I0 is also supported from the structure IS. The manner of supporting the stator casing and the casing of the centrifugal compressor from the structure l9 will be described hereinafter.
  • the structure [9 comprises a truncated conical member 2
  • the latter are secured to the central member 2
  • Each end piece 22, 23 slopes upwardly from the central member 2
  • the flange 24 is secured, as by bolts 3'
  • the mounting ring (as is clear from Figure 1) encircles the power-plant and is attached to the aeroplane by means of a rigid tubular structure (not shown).
  • This rigidity is further increased by having a plurality of beam members 21 which extend lengthwise of the support structure I9 and generally radially thereof. The members 21 are secured to the central member 2! and the end pieces 22 and 23 of the support structure.
  • each combustion chamber I lies within the structure I9 and between a pair of adjacent beams 21.
  • the end pieces 22 and 23 are formed with aplurality of holes 28 through which the ducts leading to and from the combust-ion chambers pass.
  • the support structure described has a high resistance to bending since the radial depth thereof is considerable. That portion of the power-plant lying ahead of a plane containing the flange 24 and behind a plan i in th flange 25 will be carried cantileverwise from the structure l9 and the external loads to which these parts of the powerplant are subjected will not be transmitted to the stator case of the compressor 9, they will be transmitted directly to the support structure and thence to the aeroplane.
  • stator casing may therefore be designed solely to carry the loads due to the operation of the axial compressor and due to the external loads to which the stator casing alone is subjected.
  • the portion of the power-plant lying ahead of the plane passing through the flange 24 comrrises .the housing II and the ancillaries I2 to IE. That portion of the power-plant lying behind the flange 25 comprises the turbine 6, the tail pipe 8 and the discharge ends of the combustion chambers.
  • the turbine B is supported from the annular member 68 by a structure indicated by the reference numeral 29.
  • the various members of the power-plant are subjected to temperatures which vary widely. Accordingly it is considered necessary that provision be made for relative expansions between certain members of the power-plant. For instanre whilst the temperature of the working fluid entering the compressor 9 may be low (being atmospheric) the temperature in the combustion chambers 1 and in the turbine 6 is relatively very high. 7
  • Each end of the stator casing of compressor 9 is supported from the structure l9 so as to enable such expansions to take place.
  • the casing of the axial compressor 9 adjacent its point of attachment 20 to the centrifugal compressor I0 is formed with a circular flange 30.
  • and the end piece 22 at the junction thereof is an annular strip 3! the inner face of which engages with the flange 30.
  • and flange 3B permit relative movements between the casing of compressor 9 and the structure 19 in the axial direction of the power plant, radial movements, however, not being permitted.
  • the annular member I8 to which the casing of the compressor 9 is secured is supported from the mounting ring 26 so as to enjoy freedom of movement relatively thereto in the axial and radial directions.
  • the support for the member l8 comprises a plurality of links 32 which are disposed generally radially of the power-plant the inner end of each link being pivotally secured, as at 33. to the annular member I8, The outer end of each link is pivotally secured. at 35, to a stud 34 which passes througha radial collar 36 carried by the mounting ring 26.
  • annular member I 8 (and hence the stator casing attached thereto) is capable of axial movements relatively to the support structure 49 since with such movements the links 32 pivot about the point of attachment 35.
  • the relative movements between the support structure 19 and the stator casing in a radial direction are permitted by the studs 34 and their associated collars 36.
  • stator casing for the compressor 9 when a gas-turbine power-plant as described is supported in accordance with the present invention. Accordingly this casing may be formed in two or more segmental sections which are bolted together to form a joint which extends lengthwise of the power-plant. Alternatively the stator casing may, if desired, be formed in two or more sections which are joined together by one or more peripheral joints extending around the casing.
  • the combination-witha gas-turbine engine comprising a compressor assembly, an axial-flow compressor constituting part of said assembly, combustion equipment to receive air from the compressor assembly and in which fuel is burnt and a turbine to drive the compressor assembly,- said turbine, which is driven by the hot gases from the combustion equipment being supported from one end of the compressor assembly with the combustion equipment supported therebetween, of a compressor structure surrounding the axial-flow compressor, means fixing one end of the compressor structure to the compressor assembly, a connection between the other end of the compressor structure and the compressor assembl said connection allowing of relative radial and axial movements between the assembly and said structure and a cantilever structure secured to said compressor structure to support the gas turbine engine as a unit.
  • a gas-turbine engine comprising a compressor assembly, an axial-flow compressor constituting part of said assembly, combustion equipment to receive air from the compressor assembly and in which fuel is burnt and a turbine to drive the compressor assembly, said turbine which is driven by the hot gases from the combustion equipment, being supported from one end of the compressor assembly with the combustion equipment supported therebetween, of a frusto-conical member having outwardly-fiared end pieces of frusto-conical form, a mounting ring secured to one end piece, means fixing one end piece to the compressor assembly, a connection between the mounting ring and the compressor assembly said connection allowing of relative radial and axial movements between the assembly and the frusto-conical member and a cantilever structure secured to said mounting ring to support the gas turbine engine as a unit.
  • said turbine which is driven b the hot gases from the combustion equipment being supported from one end of the compressor assembly with the combustion equipment supported therebetween, of a frusto-conical member having outwardly-flared end pieces of Irusto-conical form, a. plurality of beams extending from one end piece to the other and radially disposed of the frusto-conical member, a mounting ring secured to one end piece, means fixing one end piece to the compressor assembly, a connection between the mounting ring and the compressor assembly said connection allowing of relative radial and axial movements between the assembly and the 6 frusto-conical member, and a cantilever structure secured to the mounting ring to support the gas-turbine engine as a unit.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Nov. 14, 1950 F. M. OWNER ETAL MEANS FOR SUPPORTING GAS-TURBINE POWER PLANTS 3 Sheets-Sheet 1 Filed Nov. 13, 1946 [dz/anim- Eanl fl Owner M15160 5 22M Zrz'@e gm L. 0
Nov. 14,* 1950 F. M. OWNER ETAL mams FOR SUPPORTING GAS-TURBINE POWER PLANTS Filed Nov. 13, 1946 5 Sheets-Sheet 2 N 1950 F. M. OWNER El'AL 2,529,958
MEANS FOR SUPPORTING GAS-TURBINE POWER PLANTS Filed Nov. 13, 1946 3 Sheets-Sheet 3 jvwanZZrs 3' I j ZJM W Patented Nov. 14, 1950 MEANS FOR SUPPORTING GAS-TURBINE POWER PLANTS Frank Morgan Owner tol Aeroplane Compan land, a British compa Application November 13, 1946, Serial No.
and Alec George Henstridge, Bristol, England, assixnors to The Brisy Limited, Bristol, Engy In Great Britain October 9, 1945 Section 1, Public La Patent expires This invention concerns means for supporting a gas-turbine power-plant. The object of this invention is to provide a support which enables the external loads of one or more members of the power-plant to be borne solely by said member or members. The external loads (that is, those due to weight and inertia forces) are therefore not transmitted from other members of the power-plant to said member and vice versa.
' Accordingto the present invention means for supporting a gas-turbine power-plant is attached to the power-plant atpositions spaced along the length thereof, part of the plant being supported cantileverwise of said means and part between said-attachments.
The present invention find particular appl cation to gas-turbine power plants having an ax1alflow compressor and, according to another feature of the present invention, such a power-plant is supported as described with said compressor disposed between said attachments. As a consequence the compressor is relieved of the external loads due to the other parts of the power-plant.
Thesta-tor casing may be designed, therefore, to carry the-loads due to the operation of the compressor and only the external loads of the compressor.
According to another feature of the presentinvention, that part of the power-plant which is disposed between the attachments is capable of g a limited movement relatively to the supporting structure in an axial and/or radial direction of the power-plant.
In order that the present invention may be understood a practical application will now be described by way of example with reference to the accompanying drawings whereof Figure 1 is a side elevation of a gas-turbine power-plant'having support means in accordance with the invention.
Figure 2 is a section on the line 2-2 of Figure 1 and 4 Figure 3 is a section on the line 33 of Figure 1 but to an enlarged scale.
The gas-turbine power-plant which is about to be described is adapted for the propulsion of an aeroplane and comprises a compressor unit generally indicated by the reference numeral 5, a turbine 6 for driving the compressor unit, a plurality of combustion chambers land a tail pipe 8.
The turbine 6 is disposed adjacent the tail pipe 8 (being at the rear end of the power-plant) and is connected with an axial and centrifugal compressor 9 and Ill respectively; The axial and centrifugal compressors together constitute the comw 690, August 8, 1946 October 9, 1965 3 Claims. (Cl. 604l) pressor unit 5. The compressors are disposed in line with the turbine 6 and between the latter and a housing II The latter carries a group of power plant ancillaries such as at [2, I 3, l4 and I5. It is clear from Figure 1 that these are disposed at the opposite end of the power-plant to the turbine 6, that is, at the front end of the power-plant.
The working fluid is admitted to the axial compressor between the latter and the turbine l as at l6 and thereafter the working fluid passes in succession through the axial compressor 9 and the centrifugal compressor III, which is of the two-stage type. The working fluid (during compression) therefore travels from the rear end of the power-plant to the front end where it is discharged into the combustion chambers 1. The latter are spaced around the compressor 9 and convey the working fluid rearwardly from the centrifugal compressor III to the turbine 6.
The output shaft of the turbine 6 passes through the turbine casing and is suitably connected with a shaft (not shown) which supports the rotor and impellers of the compressor unit which extends into the housing II. In this way drive is transmitted from the turbine to the compressor unit and also to the ancillaries.
The various members of. the power-plant are subjected to loads due to their operation and also to external loads due to the weight of the powerplant and as a result of the aeroplane being manoeuvred. It is desirable that the stator casing of compressor 9 be relieved of these external loads, the casing being required to carry only those loads due to the operation of the compressor and the external loads to which this stator casing alone is subjected.
That end of the stator casing which in part defines the mouth I! of the compressor 9 is attached to an annular member I8 which is itself supported from a structure IS. The delivery end of the stator casing is secured to the casing of the centrifugal compressor In as at 20. The casing of the centrifugal compressor I0 is also supported from the structure IS. The manner of supporting the stator casing and the casing of the centrifugal compressor from the structure l9 will be described hereinafter.
The structure [9 comprises a truncated conical member 2| which surrounds the stator casing of compressor 9 and a pair of end pieces 22 and 23. The latter are secured to the central member 2|, as by welding, and are themselves of truncated conical form. Each end piece 22, 23 slopes upwardly from the central member 2| to a circumferential flange 24, 25 respectively. The flange 24 is secured, as by bolts 3'|, to the casing of the centrifugal, compressor l0 and the. flange 25 is welded to a mounting ring 26. The mounting ring (as is clear from Figure 1) encircles the power-plant and is attached to the aeroplane by means of a rigid tubular structure (not shown).
The depth from the attachment flanges 24, 25 to the central member 2| ls considerable in order that the structure [9 may possess the required rigidity. This rigidity is further increased by having a plurality of beam members 21 which extend lengthwise of the support structure I9 and generally radially thereof. The members 21 are secured to the central member 2! and the end pieces 22 and 23 of the support structure.
With a view to reducing the overall diameter of the power-plant each combustion chamber I lies within the structure I9 and between a pair of adjacent beams 21. The end pieces 22 and 23 are formed with aplurality of holes 28 through which the ducts leading to and from the combust-ion chambers pass.
The support structure described has a high resistance to bending since the radial depth thereof is considerable. That portion of the power-plant lying ahead of a plane containing the flange 24 and behind a plan i in th flange 25 will be carried cantileverwise from the structure l9 and the external loads to which these parts of the powerplant are subjected will not be transmitted to the stator case of the compressor 9, they will be transmitted directly to the support structure and thence to the aeroplane. The
stator casing may therefore be designed solely to carry the loads due to the operation of the axial compressor and due to the external loads to which the stator casing alone is subjected.
The portion of the power-plant lying ahead of the plane passing through the flange 24 comrrises .the housing II and the ancillaries I2 to IE. That portion of the power-plant lying behind the flange 25 comprises the turbine 6, the tail pipe 8 and the discharge ends of the combustion chambers. The turbine B is supported from the annular member 68 by a structure indicated by the reference numeral 29.
The various members of the power-plant are subjected to temperatures which vary widely. Accordingly it is considered necessary that provision be made for relative expansions between certain members of the power-plant. For instanre whilst the temperature of the working fluid entering the compressor 9 may be low (being atmospheric) the temperature in the combustion chambers 1 and in the turbine 6 is relatively very high. 7
Each end of the stator casing of compressor 9 is supported from the structure l9 so as to enable such expansions to take place. The casing of the axial compressor 9 adjacent its point of attachment 20 to the centrifugal compressor I0 is formed with a circular flange 30. Secured to the central member 2| and the end piece 22 at the junction thereof is an annular strip 3! the inner face of which engages with the flange 30. The strip 3| and flange 3B permit relative movements between the casing of compressor 9 and the structure 19 in the axial direction of the power plant, radial movements, however, not being permitted.
The annular member I8 to which the casing of the compressor 9 is secured is supported from the mounting ring 26 so as to enjoy freedom of movement relatively thereto in the axial and radial directions. The support for the member l8 comprises a plurality of links 32 which are disposed generally radially of the power-plant the inner end of each link being pivotally secured, as at 33. to the annular member I8, The outer end of each link is pivotally secured. at 35, to a stud 34 which passes througha radial collar 36 carried by the mounting ring 26.
With such an arrangement the annular member I 8 (and hence the stator casing attached thereto) is capable of axial movements relatively to the support structure 49 since with such movements the links 32 pivot about the point of attachment 35. The relative movements between the support structure 19 and the stator casing in a radial direction are permitted by the studs 34 and their associated collars 36.
Considerable freedom is allowed in the design of the stator casing for the compressor 9 when a gas-turbine power-plant as described is supported in accordance with the present invention. Accordingly this casing may be formed in two or more segmental sections which are bolted together to form a joint which extends lengthwise of the power-plant. Alternatively the stator casing may, if desired, be formed in two or more sections which are joined together by one or more peripheral joints extending around the casing.
We claim:
l. The combination-witha gas-turbine engine comprising a compressor assembly, an axial-flow compressor constituting part of said assembly, combustion equipment to receive air from the compressor assembly and in which fuel is burnt and a turbine to drive the compressor assembly,- said turbine, which is driven by the hot gases from the combustion equipment being supported from one end of the compressor assembly with the combustion equipment supported therebetween, of a compressor structure surrounding the axial-flow compressor, means fixing one end of the compressor structure to the compressor assembly, a connection between the other end of the compressor structure and the compressor assembl said connection allowing of relative radial and axial movements between the assembly and said structure and a cantilever structure secured to said compressor structure to support the gas turbine engine as a unit.
2. The combination with a gas-turbine engine comprising a compressor assembly, an axial-flow compressor constituting part of said assembly, combustion equipment to receive air from the compressor assembly and in which fuel is burnt and a turbine to drive the compressor assembly, said turbine which is driven by the hot gases from the combustion equipment, being supported from one end of the compressor assembly with the combustion equipment supported therebetween, of a frusto-conical member having outwardly-fiared end pieces of frusto-conical form, a mounting ring secured to one end piece, means fixing one end piece to the compressor assembly, a connection between the mounting ring and the compressor assembly said connection allowing of relative radial and axial movements between the assembly and the frusto-conical member and a cantilever structure secured to said mounting ring to support the gas turbine engine as a unit.
3. The combination with a gas-turbine engine comprising a compressor assembly, an axial-flow compressor constituting part of said assembly, combustion equipment to receive air from the compressor assembly and in which fuel is burnt 76 and a turbine to drive the compressor assembly,
5 said turbine which is driven b the hot gases from the combustion equipment being supported from one end of the compressor assembly with the combustion equipment supported therebetween, of a frusto-conical member having outwardly-flared end pieces of Irusto-conical form, a. plurality of beams extending from one end piece to the other and radially disposed of the frusto-conical member, a mounting ring secured to one end piece, means fixing one end piece to the compressor assembly, a connection between the mounting ring and the compressor assembly said connection allowing of relative radial and axial movements between the assembly and the 6 frusto-conical member, and a cantilever structure secured to the mounting ring to support the gas-turbine engine as a unit.
FRANK MORGAN OWNER. ALEC GEORGE HENSTRIDGE.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 2,410,450 Kroon Nov. 5, 1946
US709522A 1945-10-09 1946-11-13 Means for supporting gas-turbine power plants Expired - Lifetime US2529958A (en)

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2676459A (en) * 1947-06-12 1954-04-27 Bristol Aeroplane Co Ltd Gas turbine engine having a continuous outer stress bearing shell and means allowing access through the shell to the combustion space of the engine
US2687860A (en) * 1949-04-13 1954-08-31 Chrysler Corp Mounting
US2738647A (en) * 1951-07-03 1956-03-20 Boeing Co Gas turbine engine frame structure
US2763462A (en) * 1950-01-11 1956-09-18 Gen Motors Corp Turbine casing construction
US2828939A (en) * 1950-09-20 1958-04-01 Power Jets Res & Dev Ltd Support of turbine casings and other structure
US2928535A (en) * 1953-07-14 1960-03-15 Walter A Simmons Shock-resisting support for storing and shipping engines and the like equipment containing destructible components
US3327473A (en) * 1966-01-11 1967-06-27 Gen Motors Corp Engine support structure
FR2500905A1 (en) * 1981-03-02 1982-09-03 Gen Electric REAR MOUNTING SYSTEM FOR TRANSITION CHANNEL ELEMENTS
US5996334A (en) * 1997-09-29 1999-12-07 Solar Turbines Gas turbine engine having an external central frame
US20050000227A1 (en) * 2003-07-02 2005-01-06 Mccaffrey Timothy P. Methods and apparatus for operating gas turbine engine combustors
US20050116093A1 (en) * 2003-12-01 2005-06-02 Airbus France Mounting structure for mounting a turboprop under an aircraft wing
US20090175716A1 (en) * 2008-01-08 2009-07-09 Rolls-Royce North American Technologies, Inc. Integrated bypass engine structure

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2410450A (en) * 1943-01-30 1946-11-05 Westinghouse Electric Corp Turbine apparatus

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2410450A (en) * 1943-01-30 1946-11-05 Westinghouse Electric Corp Turbine apparatus

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2676459A (en) * 1947-06-12 1954-04-27 Bristol Aeroplane Co Ltd Gas turbine engine having a continuous outer stress bearing shell and means allowing access through the shell to the combustion space of the engine
US2687860A (en) * 1949-04-13 1954-08-31 Chrysler Corp Mounting
US2763462A (en) * 1950-01-11 1956-09-18 Gen Motors Corp Turbine casing construction
US2828939A (en) * 1950-09-20 1958-04-01 Power Jets Res & Dev Ltd Support of turbine casings and other structure
US2738647A (en) * 1951-07-03 1956-03-20 Boeing Co Gas turbine engine frame structure
US2928535A (en) * 1953-07-14 1960-03-15 Walter A Simmons Shock-resisting support for storing and shipping engines and the like equipment containing destructible components
US3327473A (en) * 1966-01-11 1967-06-27 Gen Motors Corp Engine support structure
US4422288A (en) * 1981-03-02 1983-12-27 General Electric Company Aft mounting system for combustion transition duct members
FR2500905A1 (en) * 1981-03-02 1982-09-03 Gen Electric REAR MOUNTING SYSTEM FOR TRANSITION CHANNEL ELEMENTS
US5996334A (en) * 1997-09-29 1999-12-07 Solar Turbines Gas turbine engine having an external central frame
US20050000227A1 (en) * 2003-07-02 2005-01-06 Mccaffrey Timothy P. Methods and apparatus for operating gas turbine engine combustors
US7093419B2 (en) * 2003-07-02 2006-08-22 General Electric Company Methods and apparatus for operating gas turbine engine combustors
US20050116093A1 (en) * 2003-12-01 2005-06-02 Airbus France Mounting structure for mounting a turboprop under an aircraft wing
US7159819B2 (en) * 2003-12-01 2007-01-09 Airbus France Mounting structure for mounting a turboprop under an aircraft wing
US20090175716A1 (en) * 2008-01-08 2009-07-09 Rolls-Royce North American Technologies, Inc. Integrated bypass engine structure
US8438859B2 (en) * 2008-01-08 2013-05-14 Rolls-Royce North American Technologies, Inc. Integrated bypass engine structure

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