US3737247A - Composite nozzle - Google Patents

Composite nozzle Download PDF

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Publication number
US3737247A
US3737247A US00133002A US3737247DA US3737247A US 3737247 A US3737247 A US 3737247A US 00133002 A US00133002 A US 00133002A US 3737247D A US3737247D A US 3737247DA US 3737247 A US3737247 A US 3737247A
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Prior art keywords
nozzle
spaced
ring
passages
nozzle ring
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Expired - Lifetime
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US00133002A
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W Horning
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N & R FUNDING CORP A CORP OF
Garrett Corp
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Garrett Corp
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines

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  • the present invention provides a composite nozzle having an outer nozzle ring of an easily machinable material to provide close dimensional tolerances for the nozzle passage therethrough and an inner nozzle ring of erosion resistant material with slightly larger nozzle passages therethrough and having relaxed tolerances.
  • FIG. 1 is a partial sectional view of a radial inward flow turbine illustrating the composite nozzle of the present invention.
  • FIG. 2 is a sectional view of the composite nozzle portion of the radial inward flow turbine of FIG. 1 taken along line 2-2.
  • FIG. 3 is a sectional view of the composite nozzle of FIG. 2 taken along line 33.
  • the radial inward flow turbine generally comprises a torus assembly mounted between supports 12, 14 positioned on a turbine nozzle 16. Packings 18 and may be provided between the nozzle 16 and the supports 12 and 14 respectively.
  • the nozzle 16 having an outer nozzle ring 17 may be constructed of any easily machinable material, such as steel, which can be fabricated to close dimensional tolerances.
  • a turbine wheel 21 including blades 22 is adapted to rotate between the nozzle 16 and a seal 24.
  • the inner nozzle ring 26 may be held in position by a groove 28 in the nozzle 16 and/or by a plurality of screws 30 (and washers 32) threaded into the outer nozzle ring 17.
  • An elastomeric seal such as silicone rubber cement, may be provided between mating surfaces of the outer nozzle ring 17 and inner nozzle ring 26.
  • the seal 24 extends upward between the nozzle 16 and the turbine housing assembly 34. Shims 36 and 38 can be provided between this upward extending seal 24 and the housing assembly 34 and inner nozzle ring 26, respectively.
  • At least one row of spaced nozzle passages 40 extend around the outer nozzle ring 17. Two rows of individually staggered passages 40 are illustrated. These passages 40 may be provided with an enlarged tapered inlet section 42 to facilitate flow entry. Aligned with the individual passages 40 in outer nozzle ring 17 are a plurality of individual passages 44 in the inner nozzle ring 26. With the nozzle 16 including outer nozzle ring 17 constructed of an easily fabricated material such as steel,
  • the nozzle passages 40 can be machined to a precise dimension holding close tolerances, sufficient to control the turbine flow rate as required.
  • the inner nozzle ring 26, being constructed of an erosion resistant material, is not susceptible to being machined to close tolerances and, accordingly, the flow area of individual nozzle passages 44 should be slightly greater than the flow area of individual nozzle passages 40.
  • the diameter of nozzle passages 40 is designated as D, having a'tolerance of T
  • the diameter D, of nozzle passages 44 would be slightly greater than D and have a tolerance T considerably greater than tolerance T, with the limitation that (D T is still greater than or equal to (D, T,).
  • the erosion resistant material is provided in the area where it is required, thus greatly enhancing the nozzle life.
  • erosion damage to the turbine wheel is also reduced.
  • the composite nozzle can be economically produced, since relatively large dimensional tolerances can be accommodated by the erosion resistant material.
  • the nozzle throat which controls the turbine flow rate is incorporated into the outer nozzle ring which can be fabricated to close dimensional tolerances.
  • a composite nozzle for a radial inward flow turbine wheel comprising:
  • an inner nozzle ring of an erosion resistant material disposed radially inward from the outer nozzle ring and having a plurality of spaced nozzle passages extending therethrough individually aligned with the spaced nozzle passages of said outer nozzle ring to receive a flow of fluid therefrom, said inner nozzle ring radially disposed around said turbine wheel to deliver a flow of fluid thereto.
  • a composite nozzle for a radial inward flow turbine wheel comprising:
  • an outer nozzle ring having a plurality of spaced nozzle passages extending therethrough, said outer nozzle ring spaced nozzle passages having a crosssectional flow dimension D with a dimensional tolerance T,;
  • an inner nozzle ring of an erosion resistant material disposed radially inward from the outer nozzle ring and having a plurality of spaced nozzle passages extending therethrough individually aligned with the spaced nozzle passages of said outer nozzle ring, said inner nozzle ring spaced nozzle passages receiving a flow of fluid from said spaced nozzle passages of said outer nozzle ring and having a crosssectional flow dimension D, greater than D and with a dimensional tolerance T greater than T such that D, T is at least equal to D, T, said inner nozzle ring radially disposed around said turbine wheel to deliver a flow of fluid thereto.
  • a turbine housing to rotatably support said turbine wheel therein and direct the flow of fluid thereto, said turbine housing including a composite nozzle radially disposed around said turbine wheel to direct the flow of fluid from said housing to said radial turbine wheel;
  • said composite nozzle comprising an outer nozzle ring having a plurality of spaced nozzle passages extending therethrough and an inner nozzle ring of an erosion resistant material disposed radially inward from said outer nozzle ring and having a plu- I ralityof spaced nozzle passages extending therethrough individually aligned with the spaced nozzle passages of said outer nozzle ring, the flow of fluid from said turbine housing to said radial turbine wheel being first through the spaced nozzle passages of said outer nozzle ring and then through the spaced nozzle passages of said inner nozzle ring.
  • the spaced nozzle passages of said inner nozzle ring are substantially the same cross-sectional configuration as the spaced nozzle passages of said outer nozzle ring.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A composite turbine nozzle is provided with an erosion resistant inner surface.

Description

O United States Patem 3,737,247 Horning June 5, 1973 [54] COMPOSITE NOZZLE [56] References Cited [75] Inventor: William A. Homing, Los Angeles, UNITED STATES PATENTS Calif.
1,378,746 5/1921 Wheeler ..415/186 [73] Asslgnee: The Garrett Corporatlon, Los An- 3 030 071 4/1962 s h -Jn .415/196 geles, Calif. 3,042,366 7/1963 l-lolmquist ....4l5/214 3,063,673 11/1962 Johnson ..415/205 [221 Filed 1971 FOREIGN PATENTS OR APPLICATIONS [21] App]. No.: 133,002 19,632 0/1905 Great Britain ..415/212 55,579 11/1943 Netherlands ..415/158 52 U.S. Cl. .415/195, 415/205, 415/212, Primary Examine, flemy R Raduazo 41 5/216 Attorney-A1bert J. Miller and John N. Hazelwood [51] Int. Cl. ..F0ld 1/08 [58] Field of Search ..415/195, 196,200, ABSTRACT 415/186, 212, 214, 219, 217, 218, 216,158, A composite turbine nozzle is provided with an erosion resistant inner surface.
14 Claims, 3 Drawing Figures PATENTEUJUN 5137s .r/WE/vrae TV/iL/AM A. Ham/W5;
when 3. 77mm J a m COMPOSITE NOZZLE BACKGROUND OF THE INVENTION In radial inward flow turbine nozzles, erosion of the inner surface of the nozzle by dirt and/or liquid particles thrown outward by the turbine wheel blades can greatly reduce the life of the nozzle. Attempts to provide a nozzle of erosion resistant material have proven to be uneconomical in view of the close dimensional tolerances required in order to control the turbine flow rate through the nozzle passages.
SUMMARY OF THE INVENTION The present invention provides a composite nozzle having an outer nozzle ring of an easily machinable material to provide close dimensional tolerances for the nozzle passage therethrough and an inner nozzle ring of erosion resistant material with slightly larger nozzle passages therethrough and having relaxed tolerances.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a partial sectional view of a radial inward flow turbine illustrating the composite nozzle of the present invention.
FIG. 2 is a sectional view of the composite nozzle portion of the radial inward flow turbine of FIG. 1 taken along line 2-2.
FIG. 3 is a sectional view of the composite nozzle of FIG. 2 taken along line 33.
DESCRIPTION OF THE PREFERRED EMBODIMENTS As illustrated in FIG. 1, the radial inward flow turbine generally comprises a torus assembly mounted between supports 12, 14 positioned on a turbine nozzle 16. Packings 18 and may be provided between the nozzle 16 and the supports 12 and 14 respectively. The nozzle 16 having an outer nozzle ring 17 may be constructed of any easily machinable material, such as steel, which can be fabricated to close dimensional tolerances. A turbine wheel 21 including blades 22 is adapted to rotate between the nozzle 16 and a seal 24.
The inner nozzle ring 26, of an erosion resistant material such as cemented carbide, or other sintered material such as aluminum oxide, is provided between the radial outward end of the turbine blades 22 and the outer nozzle ring 17. The inner nozzle ring 26 may be held in position by a groove 28 in the nozzle 16 and/or by a plurality of screws 30 (and washers 32) threaded into the outer nozzle ring 17. An elastomeric seal, such as silicone rubber cement, may be provided between mating surfaces of the outer nozzle ring 17 and inner nozzle ring 26. The seal 24 extends upward between the nozzle 16 and the turbine housing assembly 34. Shims 36 and 38 can be provided between this upward extending seal 24 and the housing assembly 34 and inner nozzle ring 26, respectively.
As shown more clearly in FIGS. 2 and 3, at least one row of spaced nozzle passages 40 extend around the outer nozzle ring 17. Two rows of individually staggered passages 40 are illustrated. These passages 40 may be provided with an enlarged tapered inlet section 42 to facilitate flow entry. Aligned with the individual passages 40 in outer nozzle ring 17 are a plurality of individual passages 44 in the inner nozzle ring 26. With the nozzle 16 including outer nozzle ring 17 constructed of an easily fabricated material such as steel,
the nozzle passages 40 can be machined to a precise dimension holding close tolerances, sufficient to control the turbine flow rate as required. The inner nozzle ring 26, being constructed of an erosion resistant material, is not susceptible to being machined to close tolerances and, accordingly, the flow area of individual nozzle passages 44 should be slightly greater than the flow area of individual nozzle passages 40.
For example, if the diameter of nozzle passages 40 is designated as D, having a'tolerance of T,, the diameter D, of nozzle passages 44 would be slightly greater than D and have a tolerance T considerably greater than tolerance T,, with the limitation that (D T is still greater than or equal to (D, T,).
In this way the erosion resistant material is provided in the area where it is required, thus greatly enhancing the nozzle life. In addition, erosion damage to the turbine wheel is also reduced. The composite nozzle can be economically produced, since relatively large dimensional tolerances can be accommodated by the erosion resistant material. The nozzle throat which controls the turbine flow rate is incorporated into the outer nozzle ring which can be fabricated to close dimensional tolerances.
While specific embodiments of the invention have been illustrated and described, it is to be understood that these embodiments are provided by way of example only and that the invention is not to be construed as being limited thereto, but only by the proper scope of the following claims.
What I claim is:
1. A composite nozzle for a radial inward flow turbine wheel comprising:
an outer nozzle ring having a plurality of spaced nozzle passages extending therethrough; and
an inner nozzle ring of an erosion resistant material disposed radially inward from the outer nozzle ring and having a plurality of spaced nozzle passages extending therethrough individually aligned with the spaced nozzle passages of said outer nozzle ring to receive a flow of fluid therefrom, said inner nozzle ring radially disposed around said turbine wheel to deliver a flow of fluid thereto.
2. The composite nozzle of claim 1 wherein the spaced nozzle passages of said inner nozzle ring have a greater cross-sectional flow area than the spaced nozzle passages of said outer nozzle ring.
3. A composite nozzle for a radial inward flow turbine wheel comprising:
an outer nozzle ring having a plurality of spaced nozzle passages extending therethrough, said outer nozzle ring spaced nozzle passages having a crosssectional flow dimension D with a dimensional tolerance T,; and
an inner nozzle ring of an erosion resistant material disposed radially inward from the outer nozzle ring and having a plurality of spaced nozzle passages extending therethrough individually aligned with the spaced nozzle passages of said outer nozzle ring, said inner nozzle ring spaced nozzle passages receiving a flow of fluid from said spaced nozzle passages of said outer nozzle ring and having a crosssectional flow dimension D, greater than D and with a dimensional tolerance T greater than T such that D, T is at least equal to D, T, said inner nozzle ring radially disposed around said turbine wheel to deliver a flow of fluid thereto.
4. The composite nozzle of claim 3 wherein D T is greater than D T y S. The composite nozzle of claim 3 and in addition elastomeric seal means disposed between said outer nozzle ring and said inner nozzle ring.
6. The composite nozzle of claim 3 wherein the spaced nozzle passages of said outer nozzle ring have an enlarged tapered inlet section.
7. The composite nozzle of claim 3 wherein said plurality of spaced nozzle passages comprise two circumferential rows of staggered nozzle passages.
8. The composite nozzle of claim 3 wherein said inner nozzle ring is a sintered material.
9. The composite nozzle of claim 5 wherein said elastomeric seal means is a silicone rubber cement.
10. The composite nozzle of claim 1 wherein the spaced nozzle passages extending through said inner nozzle ring are substantially the same cross-sectional configuration as the spaced nozzle passages extending through said outer nozzle ring.
11. The composite nozzle of claim 3 wherein the spaced nozzle passages extending through said inner nozzle ring are substantially the same cross-sectional configuration as the spaced nozzle passages extending through said outer nozzle ring.
12. In combination:
a radial turbine wheel; and
a turbine housing to rotatably support said turbine wheel therein and direct the flow of fluid thereto, said turbine housing including a composite nozzle radially disposed around said turbine wheel to direct the flow of fluid from said housing to said radial turbine wheel;
said composite nozzle comprising an outer nozzle ring having a plurality of spaced nozzle passages extending therethrough and an inner nozzle ring of an erosion resistant material disposed radially inward from said outer nozzle ring and having a plu- I ralityof spaced nozzle passages extending therethrough individually aligned with the spaced nozzle passages of said outer nozzle ring, the flow of fluid from said turbine housing to said radial turbine wheel being first through the spaced nozzle passages of said outer nozzle ring and then through the spaced nozzle passages of said inner nozzle ring. 13. The combination of claim 12 wherein the spaced nozzle passages of said inner nozzle ring are substantially the same cross-sectional configuration as the spaced nozzle passages of said outer nozzle ring.
14. The composite nozzle of claim 13 wherein the spaced nozzle passages of said inner nozzle ring have a greater cross-sectional flow area than the spaced nozzle passages of said outer nozzle ring.

Claims (14)

1. A composite nozzle for a radial inward flow turbine wheel comprising: an outer nozzle ring having a plurality of spaced nozzle passages extending therethrough; and an inner nozzle ring of an erosion resistant material disposed radially inward from the outer nozzle ring and having a plurality of spaced nozzle passages extending therethrough individually aligned with the spaced nozzle passages of said outer nozzle ring to receive a flow of fluid therefrom, said inner nozzle ring radially disposed around said turbine wheel to deliver a flow of fluid thereto.
2. The composite nozzle of claim 1 wherein the spaced nozzle passages of said inner nozzle ring have a greater cross-sectional flow area than the spaced nozzle passages of said outer nozzle ring.
3. A composite nozzle for a radial inward flow turbine wheel comprising: an outer nozzle ring having a plurality of spaced nozzle passages extending therethrough, said outer nozzle ring spaced nozzle passages having a cross-sectional flow dimension D1 with a dimensional tolerance T1; and an inner nozzle ring of an erosion resistant material disposed radially inward from the outer nozzle ring and having a plurality of spaced nozzle passages extending therethrough individually aligned with the spaced nozzle passages of said outer nozzle ring, said inner nozzle ring spaced nozzle passages receiving a flow of fluid from said spaced nozzle passages of said outer nozzle ring and having a cross-sectional flow dimension D2 greater than D1 and with a dimensional tolerance T2 greater than T1 such that D2 - T2 is at least equal to D1 + T1 , said inner nozzle ring radially disposed around said turbine wheel to deliver a flow of fluid thereto.
4. The composite nozzle of claim 3 wherein D2 - T2 is greater than D1 + T1.
5. The composite nozzle of claim 3 and in addition elastomeric seal means disposed between said outer nozzle ring and said inner nozzle ring.
6. The composite nozzle of claim 3 wherein the spaced nozzle passages of said outer nozzle ring have an enlarged tapered inlet section.
7. The composite nozzle of claim 3 wherein said plurality of spaced nozzle passages comprise two circumferential rows of staggered nozzle passages.
8. The composite nozzle of claim 3 wherein said inner nozzle ring is a sintered material.
9. The composite nozzle of claim 5 wherein said elastomeric seal means is a silicone rubber cemenT.
10. The composite nozzle of claim 1 wherein the spaced nozzle passages extending through said inner nozzle ring are substantially the same cross-sectional configuration as the spaced nozzle passages extending through said outer nozzle ring.
11. The composite nozzle of claim 3 wherein the spaced nozzle passages extending through said inner nozzle ring are substantially the same cross-sectional configuration as the spaced nozzle passages extending through said outer nozzle ring.
12. In combination: a radial turbine wheel; and a turbine housing to rotatably support said turbine wheel therein and direct the flow of fluid thereto, said turbine housing including a composite nozzle radially disposed around said turbine wheel to direct the flow of fluid from said housing to said radial turbine wheel; said composite nozzle comprising an outer nozzle ring having a plurality of spaced nozzle passages extending therethrough and an inner nozzle ring of an erosion resistant material disposed radially inward from said outer nozzle ring and having a plurality of spaced nozzle passages extending therethrough individually aligned with the spaced nozzle passages of said outer nozzle ring, the flow of fluid from said turbine housing to said radial turbine wheel being first through the spaced nozzle passages of said outer nozzle ring and then through the spaced nozzle passages of said inner nozzle ring.
13. The combination of claim 12 wherein the spaced nozzle passages of said inner nozzle ring are substantially the same cross-sectional configuration as the spaced nozzle passages of said outer nozzle ring.
14. The composite nozzle of claim 13 wherein the spaced nozzle passages of said inner nozzle ring have a greater cross-sectional flow area than the spaced nozzle passages of said outer nozzle ring.
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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4066381A (en) * 1976-07-19 1978-01-03 Hydragon Corporation Turbine stator nozzles
US4591312A (en) * 1983-08-22 1986-05-27 Electric Power Research Institute Particle laden fluid powered gas turbine and like apparatus and method of operation
DE4113830A1 (en) * 1991-04-27 1992-10-29 Klein Schanzlin & Becker Ag SHARED GUIDE
US5252027A (en) * 1990-10-30 1993-10-12 Carrier Corporation Pipe diffuser structure
US5964574A (en) * 1997-01-29 1999-10-12 Asea Brown Boveri Ag Exhaust-gas turbine of a turbocharger
EP1579107A4 (en) * 2002-11-13 2006-05-03 Utc Power Llc Turbine with vaned nozzles
EP1567750A4 (en) * 2002-11-13 2007-11-14 Utc Power Llc Organic rankine cycle waste heat applications
US20150056067A1 (en) * 2012-05-29 2015-02-26 Ihi Corporation Variable nozzle unit and variable-geometry turbocharger
CN114776403A (en) * 2021-12-29 2022-07-22 东方电气集团东方汽轮机有限公司 Air inlet structure and method suitable for large enthalpy drop small-flow turbine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL55579C (en) *
GB190519632A (en) * 1904-09-28 1905-12-21 Carl Semmler Expansion Nozzle for Turbines Operated by Steam and Hot Gases.
US1378746A (en) * 1920-06-21 1921-05-17 Frank A Wheeler Air-turbine
US3030071A (en) * 1959-09-22 1962-04-17 Gen Electric Erosion-resistant turbine blade
US3042366A (en) * 1958-05-05 1962-07-03 Holmquist Ernst Rudolf Magnus Axial flow gas turbine
US3063673A (en) * 1958-10-20 1962-11-13 Caterpillar Tractor Co Centripetal turbine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL55579C (en) *
GB190519632A (en) * 1904-09-28 1905-12-21 Carl Semmler Expansion Nozzle for Turbines Operated by Steam and Hot Gases.
US1378746A (en) * 1920-06-21 1921-05-17 Frank A Wheeler Air-turbine
US3042366A (en) * 1958-05-05 1962-07-03 Holmquist Ernst Rudolf Magnus Axial flow gas turbine
US3063673A (en) * 1958-10-20 1962-11-13 Caterpillar Tractor Co Centripetal turbine
US3030071A (en) * 1959-09-22 1962-04-17 Gen Electric Erosion-resistant turbine blade

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4066381A (en) * 1976-07-19 1978-01-03 Hydragon Corporation Turbine stator nozzles
US4591312A (en) * 1983-08-22 1986-05-27 Electric Power Research Institute Particle laden fluid powered gas turbine and like apparatus and method of operation
US5252027A (en) * 1990-10-30 1993-10-12 Carrier Corporation Pipe diffuser structure
DE4113830A1 (en) * 1991-04-27 1992-10-29 Klein Schanzlin & Becker Ag SHARED GUIDE
US5964574A (en) * 1997-01-29 1999-10-12 Asea Brown Boveri Ag Exhaust-gas turbine of a turbocharger
EP1579107A4 (en) * 2002-11-13 2006-05-03 Utc Power Llc Turbine with vaned nozzles
EP1567750A4 (en) * 2002-11-13 2007-11-14 Utc Power Llc Organic rankine cycle waste heat applications
US20150056067A1 (en) * 2012-05-29 2015-02-26 Ihi Corporation Variable nozzle unit and variable-geometry turbocharger
US9618005B2 (en) * 2012-05-29 2017-04-11 Ihi Corporation Variable nozzle unit and variable-geometry turbocharger
CN114776403A (en) * 2021-12-29 2022-07-22 东方电气集团东方汽轮机有限公司 Air inlet structure and method suitable for large enthalpy drop small-flow turbine
CN114776403B (en) * 2021-12-29 2023-12-26 东方电气集团东方汽轮机有限公司 An air inlet structure and method suitable for turbines with large enthalpy drop and small flow rate

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Owner name: N & R FUNDING CORP., 976 MARKET STREET EXTENSION,

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:CONGOLEUM CORPORATION A CORP. OF DE;REEL/FRAME:004300/0888

Effective date: 19840601