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US3869864A - Combustion chambers for gas turbine engines - Google Patents

Combustion chambers for gas turbine engines Download PDF

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Publication number
US3869864A
US3869864A US368576A US36857673A US3869864A US 3869864 A US3869864 A US 3869864A US 368576 A US368576 A US 368576A US 36857673 A US36857673 A US 36857673A US 3869864 A US3869864 A US 3869864A
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Prior art keywords
wall
flame tube
apertures
baffles
air
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Expired - Lifetime
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US368576A
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George Edward Bunn
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Northrop Grumman Properties Ltd
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Lucas Aerospace Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow

Definitions

  • a combust1on chamber for a gas turbine engine comep ma mam prises a flame tube surrounded by an air passage, fuel sprayer(s) at one end of the flame tube and a combus- 60/3965 gg g 'i'g tion gas outlet at the end.
  • a number of sets of aper- [58 66 36 tures are formed by corrugated portions of the wall to 1 0 earc cause air entering the flame tube to flow along the wall thereof.
  • Baffles project from the wall and are dis [56] References Clted posed in the flow path of the air flowing along the UNITED STATES PATENTS wall. Projections extend from the baffles substantially 2,531,810 11/1950 Fyffe 60/3965 parallel to the wall and towards the apertures formed 2,705,401 4/1955 Allen et a1. 60/3965 by the respective corrugated portions. 3,333,414 8/1967 Saintsbury 60/3965 3.653.207 4/1972 Stenger et a1 60/3965 4 Clalms, 2 Drawlng Flgllres COMBUSTION CHAMBERS FOR GAS TURBINE ENGINES This invention relates to combustion chambers for gas turbine engines.
  • a combustion chamber for a gas turbine engine comprising a flame tube, an air supply passage separated from the flame tube by a wall thereof [or of the flame tube] a plurality of apertures in the wall providing communication between the air supply passage and the interior of the flame tube some of the apertures being adapted to cause a flow of air along the wall within the flame tube baffles projecting from the wall within the flame tube for deflecting air passed, in use, along the wall from at least some of the said apertures, and projections spaced from the wall and extending from the baffles in a direction transverse to the direction of extent of the baffles whereby circulation of gas, in use, is established and maintained in the desired flow pattern.
  • some other of the apertures are adapted to cause a flow of air along the wall within theflame tube by being provided with baffles which extend substantially parallel to the wall in the vicinity of the apertures and some of the apertures are formed in portions of the wall which extend transversely to portions on either side of the wall so that air is introduced transversely with respect to said portions.
  • the baffles carrying the projections are disposed adjacent the last mentioned apertures with the projections extending towards said apertures.
  • FIG. 1 is a sectional view through part of a combustion chamber according to the present invention.
  • FIG. 2 is a section on the line A-A of FIG. 1.
  • the combustion chamber comprises an annular flame tube 1 surrounded by an annular air supply passage 2 which is separated from the flame tube l by a generally toroidal wall 3 of the flame tube 1.
  • An annular air inlet 4 serves to supply air to the air supply passage 2 and a series of fuel injectors 5 serve to inject fuel into the flame tube 1 together with primary air from the air supply passage 2.
  • the flame tube 1 is provided with an annular exhaust outlet 6.
  • the wall 3 is of fabricated construction and has formed therein series of apertures 7, 8 and 9 which provide communication between the air supply passage 2 and the interior of the flame tube.
  • the series of apertures 7 are baffled by baffles 10 so that air is introduced along the inside of the wall 3 to enhance cooling of the wall 3.
  • the series of apertures 8 are similarly baffled by means of baffles 11 to provide flow along the wall 3, but the baffles 11 direct flow of air in a direction away from the exhaust outlet 6 and towards the fuel injectors 5.
  • the series of apertures 9 are formed by a pair of annular corrugated strips 12 (see FIG. 2) disposed between adjacent, overlapping portions of the wall 3, the
  • corrugated strips 12 forming, in effect, a portion of the wall 3 which extends transversely to portions of the wall on either side thereof.
  • the series of apertures 9 are disposed to admit air into the flame tube 1 along the wall 3. It will be seen from FIG. I that the series of apertures 9 formed in the outer portion of wall 3 serve to direct air towards the fuel injectors 5 whilst the series of apertures 9 in the inner portion of the wall 3 serve to direct air from the fuel injectors 5.
  • each baffle 13 which project from the wall 3 internally of the flame tube 1 and are formed by annular strips attached at one of their sides to the wall 3 whilst the other sides thereof which extend into the flame tube 1 are provided with a series of spaced recesses 14. Furthermore, a plurality of spaced projections 15 are provided on each baffle 13 to project perpendicularly therefrom at the bases of the spaced recesses 14. It will be seen from FIG. 1 that each projection 15 extends substantially parallel to the wall 3 to which its associated baffle 13 is attached and towards the series of apertures 9 associated with the baffle 13.
  • the baffle 13 attached to the inner portion of the wall 3 is also disposed adjacent one of the series of apertures 8 so that air entering the flame tube 1 from that series of apertures 8 is deflected not only by baffle 11 associated therewith but also by the surface of the baffle l3 remote from the projections 15.
  • On the opposite sides of the baffle 13 to the series of apertures 9 on the outer portion of the wall 3 are provided a further series of apertures 16 providing direct communication between the air passage 2 and the flame tube 1, these series of apertures 16 being unbaffled and extending with their axes in a radial direction with respect to the axis of the flame tube 1.
  • a combustion chamber for a gas turbine engine comprising a flame tube, an air supply passage separated from said flame tube by a wall thereof, means defining a plurality of apertures in said wall providing communication between said air supply passage and the interior of said flame tube, each of said apertures being adapted to cause a flow of air along said wall within said flame tube, baffles projecting from said wall within said flame tube for deflecting air passed, in use, along said wall from at least some of said apertures, and projections spaced from said wall and extending from said baffles in a direction transverse to the direction of extent of said baffles whereby circulation of gas, in use, is established and maintained in the desired flow pattern.
  • baffles comprise strips each of which is attached at one side thereof to said wall within said flame tube and is provided with a series of spaced recesses at 3 4 the'other side thereoflandsaid projections extend from wall which extend transversely to wall portions on ei- Said baffles at the bases of Said recesses a direction ther side thereof so that air is introduced along the lastupstream of the respective baffles relative to the air mentioned portions whose circulation is.pro-moted thereby.
  • baffles carrying said pro ections are (115- wherein some of said apertures are adapted to cause a flow of air along said wall within said flame tube by posed adjacen?
  • said apertures f f tram being provided with baffles which extend substantially Versely extending Wall portlons Said Projections parallel to said wall in the vicinity of said apertures and tending Q dS he a -mentioned apertures.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Gas Burners (AREA)

Abstract

A combustion chamber for a gas turbine engine comprises a flame tube surrounded by an air passage, fuel sprayer(s) at one end of the flame tube and a combustion gas outlet at the end. A number of sets of apertures are formed by corrugated portions of the wall to cause air entering the flame tube to flow along the wall thereof. Baffles project from the wall and are disposed in the flow path of the air flowing along the wall. Projections extend from the baffles substantially parallel to the wall and towards the apertures formed by the respective corrugated portions.

Description

7 0 United States atent 1 1 1111 3,869,864 Bun-n Mar. 11, 1975 1 COMBUSTION CHAMBERS FOR GAS 3,671,171 6/1972 Doyle 60/3965 x TURBINE ENGINES FOREIGN PATENTS OR APPLICATIONS Inventor: George EdwardBunn, Clitheroe, 943,250 12/1963 Great Britain 60/3965 England 1,150,344 4/1969 Great Britain 60/39.65 Assigneez Lucas Aerospace Limited, 721,899 1/1955 Great Britain 60/3965 1 Blrmmgham England Primary Examiner-C. J. Husar [22] Filed: June 11, 1973 Assistant Examiner-Robert E. Garrett [211 App! NOJ 368,576 Attorney, Agent, or Firm-Holman & Stern 57 ABSTRACT [30] Foreign Application Priority Data I S t 6 1972 G t B 2715M A combust1on chamber for a gas turbine engine comep ma mam prises a flame tube surrounded by an air passage, fuel sprayer(s) at one end of the flame tube and a combus- 60/3965 gg g 'i'g tion gas outlet at the end. A number of sets of aper- [58 66 36 tures are formed by corrugated portions of the wall to 1 0 earc cause air entering the flame tube to flow along the wall thereof. Baffles project from the wall and are dis [56] References Clted posed in the flow path of the air flowing along the UNITED STATES PATENTS wall. Projections extend from the baffles substantially 2,531,810 11/1950 Fyffe 60/3965 parallel to the wall and towards the apertures formed 2,705,401 4/1955 Allen et a1. 60/3965 by the respective corrugated portions. 3,333,414 8/1967 Saintsbury 60/3965 3.653.207 4/1972 Stenger et a1 60/3965 4 Clalms, 2 Drawlng Flgllres COMBUSTION CHAMBERS FOR GAS TURBINE ENGINES This invention relates to combustion chambers for gas turbine engines.
According to the present invention, there is provided a combustion chamber for a gas turbine engine, comprising a flame tube, an air supply passage separated from the flame tube by a wall thereof [or of the flame tube] a plurality of apertures in the wall providing communication between the air supply passage and the interior of the flame tube some of the apertures being adapted to cause a flow of air along the wall within the flame tube baffles projecting from the wall within the flame tube for deflecting air passed, in use, along the wall from at least some of the said apertures, and projections spaced from the wall and extending from the baffles in a direction transverse to the direction of extent of the baffles whereby circulation of gas, in use, is established and maintained in the desired flow pattern.
Preferably, the said baffles comprise strips which are attached to the wall within the flame tube at one side thereof and are provided with a series of spaced recesses at the other side thereof and the projections extend from the baffles at the bases of the recesses in a direction upstream of the respective baffles relative to the air whose circulation is promoted thereby.
Most advantageously, some other of the apertures are adapted to cause a flow of air along the wall within theflame tube by being provided with baffles which extend substantially parallel to the wall in the vicinity of the apertures and some of the apertures are formed in portions of the wall which extend transversely to portions on either side of the wall so that air is introduced transversely with respect to said portions. Advantageously, the baffles carrying the projections are disposed adjacent the last mentioned apertures with the projections extending towards said apertures.
An embodiment of the present invention will now be described, by way of example, with reference to the accompanying drawings in which:
FIG. 1 is a sectional view through part of a combustion chamber according to the present invention, and
FIG. 2 is a section on the line A-A of FIG. 1.
Referring to the drawing, the combustion chamber comprises an annular flame tube 1 surrounded by an annular air supply passage 2 which is separated from the flame tube l by a generally toroidal wall 3 of the flame tube 1.
An annular air inlet 4 serves to supply air to the air supply passage 2 and a series of fuel injectors 5 serve to inject fuel into the flame tube 1 together with primary air from the air supply passage 2. The flame tube 1 is provided with an annular exhaust outlet 6.
The wall 3 is of fabricated construction and has formed therein series of apertures 7, 8 and 9 which provide communication between the air supply passage 2 and the interior of the flame tube. The series of apertures 7 are baffled by baffles 10 so that air is introduced along the inside of the wall 3 to enhance cooling of the wall 3. The series of apertures 8 are similarly baffled by means of baffles 11 to provide flow along the wall 3, but the baffles 11 direct flow of air in a direction away from the exhaust outlet 6 and towards the fuel injectors 5. The series of apertures 9 are formed by a pair of annular corrugated strips 12 (see FIG. 2) disposed between adjacent, overlapping portions of the wall 3, the
corrugated strips 12 forming, in effect, a portion of the wall 3 which extends transversely to portions of the wall on either side thereof. In this manner, the series of apertures 9 are disposed to admit air into the flame tube 1 along the wall 3. It will be seen from FIG. I that the series of apertures 9 formed in the outer portion of wall 3 serve to direct air towards the fuel injectors 5 whilst the series of apertures 9 in the inner portion of the wall 3 serve to direct air from the fuel injectors 5. At a location which is downstream of the series of apertures 9, there are provided respective baffles 13 which project from the wall 3 internally of the flame tube 1 and are formed by annular strips attached at one of their sides to the wall 3 whilst the other sides thereof which extend into the flame tube 1 are provided with a series of spaced recesses 14. Furthermore, a plurality of spaced projections 15 are provided on each baffle 13 to project perpendicularly therefrom at the bases of the spaced recesses 14. It will be seen from FIG. 1 that each projection 15 extends substantially parallel to the wall 3 to which its associated baffle 13 is attached and towards the series of apertures 9 associated with the baffle 13.
The baffle 13 attached to the inner portion of the wall 3 is also disposed adjacent one of the series of apertures 8 so that air entering the flame tube 1 from that series of apertures 8 is deflected not only by baffle 11 associated therewith but also by the surface of the baffle l3 remote from the projections 15. On the opposite sides of the baffle 13 to the series of apertures 9 on the outer portion of the wall 3 are provided a further series of apertures 16 providing direct communication between the air passage 2 and the flame tube 1, these series of apertures 16 being unbaffled and extending with their axes in a radial direction with respect to the axis of the flame tube 1.
It is considered that the above described combustion chamber is particularly efficient since almost all the air, some 96% is used for cooling purposes and is then deflected by the baffles 13 with projections 15, to participate in the combustion process. In contrast, in conventional arrangements about 40% of the air is introduced as cooling air which is largely confined to regions close to the flame tube wall and is not deflected to participate in the combustion process. This latter arrangement has an undesirable effect on the temperature dis tribution at the outlet of the combustion chamber.
I claim:
1. A combustion chamber for a gas turbine engine, comprising a flame tube, an air supply passage separated from said flame tube by a wall thereof, means defining a plurality of apertures in said wall providing communication between said air supply passage and the interior of said flame tube, each of said apertures being adapted to cause a flow of air along said wall within said flame tube, baffles projecting from said wall within said flame tube for deflecting air passed, in use, along said wall from at least some of said apertures, and projections spaced from said wall and extending from said baffles in a direction transverse to the direction of extent of said baffles whereby circulation of gas, in use, is established and maintained in the desired flow pattern.
2. The combustion chamber according to claim 1, wherein said baffles comprise strips each of which is attached at one side thereof to said wall within said flame tube and is provided with a series of spaced recesses at 3 4 the'other side thereoflandsaid projections extend from wall which extend transversely to wall portions on ei- Said baffles at the bases of Said recesses a direction ther side thereof so that air is introduced along the lastupstream of the respective baffles relative to the air mentioned portions whose circulation is.pro-moted thereby.
3. The combustion chamber according to claim 1, 5
wherein said baffles carrying said pro ections are (115- wherein some of said apertures are adapted to cause a flow of air along said wall within said flame tube by posed adjacen? said apertures f f tram being provided with baffles which extend substantially Versely extending Wall portlons Said Projections parallel to said wall in the vicinity of said apertures and tending Q dS he a -mentioned apertures.
some of said apertures are formed in portions of said 4. The combustion chamber according to claim 3,

Claims (4)

1. A combustion chamber for a gas turbine engine, comprising a flame tube, an air supply passage separated from said flame tube by a wall thereof, means defining a plurality of apertures in said wall providing communication between said air supply passage and the interior of said flame tube, each of said apertures being adapted to cause a flow of air along said wall within said flame tube, baffles projecting from said wall within said flame tube for deflecting air passed, in use, along said wall from at least some of said apertures, and projections spaced from said wall and extending from said baffles in a direction transverse to the direction of extent of said baffles whereby circulation of gas, in use, is established and maintained in the desired flow pattern.
1. A combustion chamber for a gas turbine engine, comprising a flame tube, an air supply passage separated from said flame tube by a wall thereof, means defining a plurality of apertures in said wall providing communication between said air supply passage and the interior of said flame tube, each of said apertures being adapted to cause a flow of air along said wall within said flame tube, baffles projecting from said wall within said flame tube for deflecting air passed, in use, along said wall from at least some of said apertures, and projections spaced from said wall and extending from said baffles in a direction transverse to the direction of extent of said baffles whereby circulation of gas, in use, is established and maintained in the desired flow pattern.
2. The combustion Chamber according to claim 1, wherein said baffles comprise strips each of which is attached at one side thereof to said wall within said flame tube and is provided with a series of spaced recesses at the other side thereof, and said projections extend from said baffles at the bases of said recesses in a direction upstream of the respective baffles relative to the air whose circulation is promoted thereby.
3. The combustion chamber according to claim 1, wherein some of said apertures are adapted to cause a flow of air along said wall within said flame tube by being provided with baffles which extend substantially parallel to said wall in the vicinity of said apertures and some of said apertures are formed in portions of said wall which extend transversely to wall portions on either side thereof so that air is introduced along the last-mentioned portions.
US368576A 1972-06-09 1973-06-11 Combustion chambers for gas turbine engines Expired - Lifetime US3869864A (en)

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GB2715472A GB1424197A (en) 1972-06-09 1972-06-09 Combustion chambers for gas turbine engines

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Cited By (32)

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Publication number Priority date Publication date Assignee Title
US4085580A (en) * 1975-11-29 1978-04-25 Rolls-Royce Limited Combustion chambers for gas turbine engines
US4195476A (en) * 1978-04-27 1980-04-01 General Motors Corporation Combustor construction
US4203283A (en) * 1977-05-25 1980-05-20 Motoren- Und Turbinen-Union Munchen Gmbh Combustion chamber, especially annular reverse-flow combustion chamber for gas turbine engines
US4211069A (en) * 1977-06-24 1980-07-08 Bbc Brown Boveri & Company Limited Combustion chamber for a gas turbine
US4244179A (en) * 1977-01-28 1981-01-13 Kainov Gennady P Annular combustion chamber for gas turbine engines
FR2479951A1 (en) * 1980-04-02 1981-10-09 United Technologies Corp INTERIOR TRIM OF COMBUSTION CHAMBER
US4765136A (en) * 1985-11-25 1988-08-23 United Technologies Corporation Gas turbine engine augmentor
WO1989006308A1 (en) * 1987-12-28 1989-07-13 Sundstrand Corporation Annular combustor with tangential cooling air injection
WO1990004089A1 (en) * 1988-10-11 1990-04-19 Sundstrand Corporation Augmented turbine combustor cooling
US4949545A (en) * 1988-12-12 1990-08-21 Sundstrand Corporation Turbine wheel and nozzle cooling
US5069033A (en) * 1989-12-21 1991-12-03 Sundstrand Corporation Radial inflow combustor
US5109671A (en) * 1989-12-05 1992-05-05 Allied-Signal Inc. Combustion apparatus and method for a turbine engine
US5113647A (en) * 1989-12-22 1992-05-19 Sundstrand Corporation Gas turbine annular combustor
US5165226A (en) * 1991-08-09 1992-11-24 Pratt & Whitney Canada, Inc. Single vortex combustor arrangement
US5237813A (en) * 1992-08-21 1993-08-24 Allied-Signal Inc. Annular combustor with outer transition liner cooling
US5271220A (en) * 1992-10-16 1993-12-21 Sundstrand Corporation Combustor heat shield for a turbine containment ring
US5628193A (en) * 1994-09-16 1997-05-13 Alliedsignal Inc. Combustor-to-turbine transition assembly
US5746048A (en) * 1994-09-16 1998-05-05 Sundstrand Corporation Combustor for a gas turbine engine
US6079199A (en) * 1998-06-03 2000-06-27 Pratt & Whitney Canada Inc. Double pass air impingement and air film cooling for gas turbine combustor walls
WO2001083963A1 (en) * 2000-05-01 2001-11-08 Elliott Energy Systems, Inc. Annular combustor for use with an energy system
US6405703B1 (en) 2001-06-29 2002-06-18 Brian Sowards Internal combustion engine
US20040088988A1 (en) * 2002-11-08 2004-05-13 Swaffar R. Glenn Gas turbine engine transition liner assembly and repair
US20060042271A1 (en) * 2004-08-27 2006-03-02 Pratt & Whitney Canada Corp. Combustor and method of providing
US20090133404A1 (en) * 2007-11-28 2009-05-28 Honeywell International, Inc. Systems and methods for cooling gas turbine engine transition liners
US20100115957A1 (en) * 2001-12-05 2010-05-13 Mandolin Financial Properties Inc. Ibc No. 613345 Combustion Chamber for A Compact Lightweight Turbine
US20100212325A1 (en) * 2009-02-23 2010-08-26 Williams International, Co., L.L.C. Combustion system
US20120328996A1 (en) * 2011-06-23 2012-12-27 United Technologies Corporation Reverse Flow Combustor Duct Attachment
US20150121886A1 (en) * 2013-03-08 2015-05-07 Rolls-Royce North American Technologies, Inc. Gas turbine engine afterburner
US20150323184A1 (en) * 2014-05-07 2015-11-12 General Electric Company Ultra compact combustor
US20230061595A1 (en) * 2021-08-30 2023-03-02 Delavan Inc. Cooling for surface ignitors in torch ignition devices
US20230064335A1 (en) * 2021-08-30 2023-03-02 Delavan Inc. Cooling for continuous ignition devices
US20230296250A1 (en) * 2022-03-21 2023-09-21 General Electric Company Turbine engine combustor and combustor liner

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DE102005008421A1 (en) * 2005-02-24 2006-08-31 Alstom Technology Ltd. Combustion chamber for a gas turbine, at a power station, has an additional air jet to give a counter flow and increase the fuel/air recirculation within the combustion zone

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US2705401A (en) * 1950-12-02 1955-04-05 Armstrong Siddeley Motors Ltd Vaporising means for liquid fuel combustion chambers
US3333414A (en) * 1965-10-13 1967-08-01 United Aircraft Canada Aerodynamic-flow reverser and smoother
US3653207A (en) * 1970-07-08 1972-04-04 Gen Electric High fuel injection density combustion chamber for a gas turbine engine
US3671171A (en) * 1970-11-27 1972-06-20 Avco Corp Annular combustors

Cited By (51)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4085580A (en) * 1975-11-29 1978-04-25 Rolls-Royce Limited Combustion chambers for gas turbine engines
US4244179A (en) * 1977-01-28 1981-01-13 Kainov Gennady P Annular combustion chamber for gas turbine engines
US4203283A (en) * 1977-05-25 1980-05-20 Motoren- Und Turbinen-Union Munchen Gmbh Combustion chamber, especially annular reverse-flow combustion chamber for gas turbine engines
US4211069A (en) * 1977-06-24 1980-07-08 Bbc Brown Boveri & Company Limited Combustion chamber for a gas turbine
US4195476A (en) * 1978-04-27 1980-04-01 General Motors Corporation Combustor construction
US4361010A (en) * 1980-04-02 1982-11-30 United Technologies Corporation Combustor liner construction
FR2479951A1 (en) * 1980-04-02 1981-10-09 United Technologies Corp INTERIOR TRIM OF COMBUSTION CHAMBER
US4765136A (en) * 1985-11-25 1988-08-23 United Technologies Corporation Gas turbine engine augmentor
USRE34962E (en) * 1987-12-28 1995-06-13 Sundstrand Corporation Annular combustor with tangential cooling air injection
WO1989006308A1 (en) * 1987-12-28 1989-07-13 Sundstrand Corporation Annular combustor with tangential cooling air injection
US4928479A (en) * 1987-12-28 1990-05-29 Sundstrand Corporation Annular combustor with tangential cooling air injection
WO1990004089A1 (en) * 1988-10-11 1990-04-19 Sundstrand Corporation Augmented turbine combustor cooling
US4944152A (en) * 1988-10-11 1990-07-31 Sundstrand Corporation Augmented turbine combustor cooling
US4949545A (en) * 1988-12-12 1990-08-21 Sundstrand Corporation Turbine wheel and nozzle cooling
US5109671A (en) * 1989-12-05 1992-05-05 Allied-Signal Inc. Combustion apparatus and method for a turbine engine
US5069033A (en) * 1989-12-21 1991-12-03 Sundstrand Corporation Radial inflow combustor
US5113647A (en) * 1989-12-22 1992-05-19 Sundstrand Corporation Gas turbine annular combustor
US5165226A (en) * 1991-08-09 1992-11-24 Pratt & Whitney Canada, Inc. Single vortex combustor arrangement
US5237813A (en) * 1992-08-21 1993-08-24 Allied-Signal Inc. Annular combustor with outer transition liner cooling
US5271220A (en) * 1992-10-16 1993-12-21 Sundstrand Corporation Combustor heat shield for a turbine containment ring
WO1994009269A1 (en) * 1992-10-16 1994-04-28 Sundstrand Corporation Combustor heat shield for a turbine containment ring
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Also Published As

Publication number Publication date
GB1424197A (en) 1976-02-11
DE2329367A1 (en) 1973-12-20
FR2188055B1 (en) 1976-09-17
IT989653B (en) 1975-06-10
FR2188055A1 (en) 1974-01-18
JPS5411844B2 (en) 1979-05-18
DE2329367C2 (en) 1981-12-24
JPS4949012A (en) 1974-05-13

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