US3845620A - Cooling film promoter for combustion chambers - Google Patents

Cooling film promoter for combustion chambers Download PDF

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Publication number
US3845620A
US3845620A US00331519A US33151973A US3845620A US 3845620 A US3845620 A US 3845620A US 00331519 A US00331519 A US 00331519A US 33151973 A US33151973 A US 33151973A US 3845620 A US3845620 A US 3845620A
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United States
Prior art keywords
pocket
cooling fluid
liner
exit
promoter
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
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US00331519A
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English (en)
Inventor
M Kenworthy
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General Electric Co
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General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US00331519A priority Critical patent/US3845620A/en
Priority to CA191,319A priority patent/CA1004047A/en
Priority to GB573474A priority patent/GB1459500A/en
Priority to DE2406277A priority patent/DE2406277C2/de
Priority to IT20387/74A priority patent/IT1006333B/it
Priority to JP49017477A priority patent/JPS5743813B2/ja
Priority to BE140804A priority patent/BE810902A/xx
Priority to FR7404680A priority patent/FR2217548B1/fr
Application granted granted Critical
Publication of US3845620A publication Critical patent/US3845620A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections

Definitions

  • the pocket includes means for diffusing the cool fluid flow within the pocket prior to passing the fluid from the exit.
  • the means for diffusing can have a variety of configurations, notably means for reversing fluid flow within the pocket and a baffle for turning the fluid prior to exit.
  • a combustion chamber liner defin ing a combustion zone also partially defines a cool fluid plenum usually circumscribing the combustion zone. Means are commonly provided for transferring a portion of the cool fluid from the plenum into the combustion zone to form the protective film barrier.”
  • means In order to accomplish effective film propagation, means must be provided for directing the fluid in a film upon the liner inner surface. This means must effectively perform attachment (that is, the disposition of the fluid in a boundary layer immediately adjacent the liner to be protected) without aspirating or entraining hot gases from the combustion zone. Such entrainment would negate the effectiveness of the film cooling by creating a turbulent interchange whereby hot gases of combustion would directly impinge the liner.
  • Effective attachment requires substantially uniform velocity cool fluid flow from the source of the film circumferentially about the liner in order to avoid excessive turbulence as well as spaced hot streaks or hot spots which naturally arise in the absence of uniform film protection.
  • the means for transferring cool fluid from the'surrounding plenum to the liner has, in the past, commonly taken the form of a plurality of spaced apertures circumferentially disposed about the liner. These apertures are used for a number of reasons. One such reason is that large mechanical stresses upon the liner require substantial mechanical strength and thus prevent a more homogeneous transfer system, such as a continuous circumferential slot or the like. Also the apertures provide a more accurate metering device than does a uniform slot.
  • the present invention alleviates these problems by providing a mechanism for substantially diffusing and coalescing the velocities of cool fluid entering through spaced, circumferential apertures from a plenum while contemporaneously enabling the use of a substantially shorter overhanging lip.
  • the present invention in one embodiment thereof, provides a combustion chamber liner which comprises a number of sections, the sections combining to define a diffusion pocket through which cool fluid passes from a circumscribing cool air plenum before reaching the heated liner surfaces to be protected.
  • the pocket is disposed and oriented with respect to the pocket entrance apertures in such a way that the cool fluid is directed initially against an opposed surface and is required to substantially reverse its direction of flow from the inlet apertures before reaching an exit from the pocket for passage onto the overhanging lip.
  • the velocity of the incoming cool fluid is diffused within the pocket by the imposition of a baffle around which the fluid must flow between the inlet apertures and the pocket exit.
  • the substantial portion of the pocket is offset from the direction imparted to the cooling film by the overhanging lip by either an angular orientation or a radial spacing, and the entrance apertures are arranged so that the incoming cool fluid must occupy the pocket prior to reaching the pocket exit for disposition upon the overhanging lip.
  • FIG. 1 depicts a combustor liner having an elongated overhanging lip according to the prior art
  • FIG. la depicts a variation of FIG. 1 illustrating a second prior art device
  • FIG. lb illustrates a further prior art variation
  • FIG. 2 depicts a cross-sectional view of a combustor incorporating a combustor liner according to the present invention
  • FIG. 3 is an enlarged perspective view of a portion of FIG. 2;
  • FIG. 4 is an enlarged cross-sectional view of a portion of FIG. 2;
  • FIG. 5 is an enlarged cross-sectional view of a portion of a combustor similar to that in FIG. 2 but with a modified version of the present invention
  • FIG. 6 is similar to FIG. 4, but with a different variation of the present invention.
  • FIG. 7 is a view similar to that in FIG. 4, but showing another variation of the present invention.
  • FIG. 8 is a view similar to that in FIG. 4, but showing still another variation of the present invention.
  • FIG. 1 A prior art cooling film promoter, disposed adjacent the heated combustion zone of a combustion chamber, is depicted in FIG. 1. It involves liner segments 10 to be protected; a relatively long overhanging lip 12 extending axially in an overlapping fashion with respect to an upstream portion of each segment 10; a substantially annular junction 14 between axially adjacent liner segments 10; a plenum 16 substantially surrounding the liner segments; and a plurality of apertures 18 providing communication between the plenum and the heated side of liner segments 10.
  • the cooling air entering the heated chamber does so in a plurality of circumferentially spaced jets with the result that fluid velocity distribution is uneven in the circumferential direction.
  • the overhanging lip 12 must be extended substantially in the axial direction downstream of apertures 18 to provide a space 20 between itself and the radially adjacent liner segment 10. This space 20 is protected by the lip from aspiration of the hot gases of the combustion chamber and provides an area for the cool fluid to coalesce by virtue of frictional engagement with wall 16 and lip 12 and to thereafter achieve attachment.
  • FIGS. la and lb depict alternative prior art devices for bringing substantially uniform circumferential fluid velocities into existence prior to disposition of a film barrier onto the liner.
  • inlet apertures 18a are angled so that cool fluid from the plenum is directed against lip 12a, to a degree, so that buffetting of the fluid against the lip reduces velocity gradients. Subsequently, the fluid is directed along the lip within space 200 where frictional forces supplement the coalescence.
  • FIG. lb differs from 1a in the angle of apertures 18]) with respect to lip 12b.
  • the cool fluid from the plenum impinges directly against lip 12b to further aid in the removal of circumferential velocity gradients.
  • the fluid is directed along space 201) where frictional engagement with lip 12b and liner segment 10b develop a fairly uniform circumferential velocity profile.
  • lip 12 detracts from its structural integrity and often leads to undesirable buckling owing to the effects of thermal stress.
  • the prior art requires this extent of lip 12, as stated, because of the danger of aspiration of hot gases and consequent breakdown of the protective film barrier.
  • FIG. 2 depicts a combustion chamber designated generally 30 and illustrating the relationship of the present invention to substantially typical combustion chambers of the gas turbine engine variety.
  • An outer liner 32 combines with an axially segmented liner 34 to define an outer plenum 36.
  • An inner liner 38 combines with an inner portion of the combustion zone liner 40 for the purpose of defining a radially inner cooling fluid plenum 42.
  • the combustion zone itself is designated 44 and is defined by liners 34 and 40 as well as by an upstream dome 46 which cooperates with a fuel nozzle 48 through which the fuel for combustion is directed into the combustion zone.
  • An air/fuel inlet 50 is defined between axial extensions 52 and 54 of liners 34 and 40, respectively.
  • combustion chamber described is substantially similar to those in present use.
  • a flow of atmospheric air is pressurized by means of a compressor (not shown) upstream of the combustion zone 44 with the compressor discharge directed partially into plena 36 and 42 as well as into the fuel/air inlet 50.
  • a quantity of fuel is mixed with the portion of air entering fuel/air inlet 50 and is ignited within combustion zone 44.
  • the rapid expansion of the burning gases and the configuration of liners 34 and 40 results in the gases being forced from combustion zone 44 through an outlet 56 and into engagement with a turbine 58.
  • Rotary portions of the turbine are driven by this exiting fluid and a portion of the energy thereof serves to drive the upstream compressor through an interconnecting shaft.
  • the remaining energy of the gas stream provides a driving thrust to the left in FIG. 2.
  • FIG. 3 illustrates a pictorial representation of a section liner 34 illustrating one embodiment of the present invention, that same embodiment being illustrated in an enlarged view in FIG. 4.
  • the figures show that liner 34 is divided substantially into a number of axially adjacent segments.
  • a typical segment 60 can be seen to be in telescopic cooperation with a typical downstream segment 62 by means of a junction designated generally 64.
  • At this junction is disposed a configuration which, in substance, comprises a cooling film promoter for passing cool fluid from plenum 36 in a protective film barrier upon the liner 34 which partially defines a hot gas passage (the combustion zone 44).
  • Segment 60 can be seen to partially define the plenum 36 as well as the combustion zone 44.
  • Segment 62 likewise, partially defines the plenum and the hot gas passage, and these liner segments cooperate to form a pocket 66 having a substantially downstream facing exit 68.
  • the pocket likewise, has an upstream closed end portion 70.
  • the pocket 66 extends circumferentially about liner 34 and thus forms a substantially annular space which is isolated from the combustion zone except for communication through exit 68.
  • the major portion of pocket 66 lies along an axis 72 angularly offset from the direction finally imparted to fluid exiting the pocket at 68.
  • the lip of the present invention (which is able to utilize this shorter axial length due to characteristics of the present invention) is substantially more mechanically reliable and is less prone to warp over extended use than similar lips of the prior art.
  • pocket 66 The basic function of pocket 66 is to provide an area substantially isolated from the combustion zone and within which velocity diffusion of the cooling fluid may occur.
  • the fluid may be directed by lip 74 in a cooling and protective film barrier upon liner 34 without the danger of turbulence and aspiration of the hot gases. Further, this is accomplished without the requirement for the relatively long overhanging lip of the prior art.
  • the present invention incorporates a plurality of circumferentially spaced apertures 76 which provide a communication between pocket 66 and plenum 64. These apertures provide a transfer means operative to deliver cool fluid (air) from the plenum 36 to the pocket in a plurality of discrete jets such that velocity gradients in the circumferential direction exist, as in the prior art, near the apertures within the pocket. It is gradients similar to these which are the basis for the requirement of the extended lip of the prior art and which, absent this lip, cause hot streaks and permit excessive turbulence and aspiration of the hot gases thus reducing the effectiveness of the protective film barrier.
  • the function of the prior art overhanging lip was not only to direct the cool fluid in a film upon the combustor liner, but also to provide an elongated axial space downstream of the cool air inlet associated with that lip so that circumferential gradients of fluid velocity could be reduced by viscous interaction with the lip itself. This was necessary so that the fluid exiting the lip would have a substantially homogeneous circumferential velocity thus reducing the likelihood of excessive turbulence, aspiration and hot streaks.
  • present invention accomplishes this same purpose by providing means for diffusing the cool fluid flow by a more effective means and in a rapid manner within pocket 66 prior to passing the cool fluid from exit 68 and onto lip 74.
  • the diffusion is accomplished by means of the relative positions of the pocket, apertures 76, wall 77 and exit 68.
  • the apertures 76 are disposed opposite and oriented to open against an opposed wall 77 of the pocket.
  • they are disposed between a substantial portion of the pocket 66 (including closed end 70) and the exit 68 relative to the flow direction of the cool fluid.
  • a portion of the cool fluid entering the pocket through the apertures is first buffetted against wall 77 and then partially reversed in its flow direction by means of engaging closed end 70 prior to passing through the exit 68.
  • This buffetting and flow reversal causes the existent velocity profiles of the fluid entering apertures 76 to be substantially broken down and coalesced or redefined in a substantially homogeneous circumferential formation as the flow leaves the closed end and traverses the length of pocket 66. In this fashion, velocity gradients in the circumferential direction are substantially eliminated by the time the fluid passes through exit 68. Thereafter, the overhanging lip 74 operates to direct the flow (in a substantially uniform circumferential velocity) as a smooth boundary layer against the heated side of the liner segment 62 downstream of the pocket 66.
  • FIG. 5 illustrates an enlarged cross-sectional view of a second embodiment of the present invention in which a pocket 66a is defined. This pocket is similar to pocket 66 of FIG. 4 in all functional respects differing there-.
  • the major portion of the pocket lies along an axis angularly offset from the final direction imparted to the cool fluid by the overhanging lip 74a.
  • the pocket has a closed end 70a upstream of the exit 68a (which opens in a downstream direction); and the transfer means includes a plurality of circumferentially spaced apertures in the liner segment, the apertures disposed downstream of the closed end and upstream of the exit and to the radially outward side of the pocket.
  • the third embodiment depicted in FIG. 6 is the same as that in FIG. 5, except that apertures 76b are disposed to the radially inward side of pocket 66b but remain downstream of closed end 70b and upstream of downstream facing exit 68b.
  • the function is to breakdown and reverse the flow direction of a portion of incoming cool fluid to provide diffusion therefor prior to engagement of overhanging lip 74b.
  • FIG. 7 depicts an embodiment of the present invention substantially different from that in FIG. 4.
  • liner segment 80 partially defines the hot gas passage as well as the plenum, and axially downstream segment 82 does likewise.
  • the two segments cooperate at a junction designated generally 84 and thereat form a pocket 86 substantially similar to that in the foregoing embodiments.
  • Means for transferring cool fluid from the plenum to the pocket include apertures 88 spaced circumferentially about the liner at junction 84.
  • a downstream facing exit 90 empties onto a relatively short overhanging lip 92.
  • Pocket 86 forms a substantially annular, axially extending space and lies downstream of apertures 88.
  • Apertures 88 are disposed between the major portion of pocket 86 (and a downstream closed end 94 thereof) and exit 90, relative to fluid flow direction. Furthermore, the major portion of pocket lies upon an axis 96 which is radially spaced from the final direction 98 imparted to the cool fluid by the overhanging lip 92.
  • cool air from the surrounding plenum is transferred through apertures 88 and into the pocket 86. Due to the directional orientation of the apertures 88, the air is directed thereby against closed end 94 and the velocities of the plurality of discrete jets of air are broken down. The flow is subsequently reversed in direction and further diffused so that the velocities coalesce. The flow is then directed and turned about baffle I02 prior to reaching exit 90. This turning of the flow further aids in the establishing of a substantially uniform circumferential velocity profile. The flow is finally directed by lip 92 as a film upon liner segment 82.
  • the cooling film promoter embodiment of FIG. 7 operates to provide a fully attached low turbulence boundary layer to serve as a barrier against the direct exposure of the segments of liner 34 and liner 40 to the extreme temperatures of the burning gases within hot gas passage 44.
  • the fact that effective diffusion of the velocities of the individual jets of cool air fed into pocket 86 occurs prior to engagement by the fluid of the overhanging lip 92 permits the use of a relatively short and structurally reliable lip while maintaining effective film propagation.
  • FIG. 8 depicts still another embodiment of the present invention which differs from that of FIG. 7 primarily in relative dimensional proportions.
  • the pocket 860 has an exit 90a which is substantially co-planar with closed end 940.
  • the overhanging lip 92a is extremely short, as is baffle 102a.
  • this embodiment it can be presumed that relatively low velocity gradients are required to be diffused within pocket 86a so that the overall dimensions of the pocket may be kept to a minimum. in function, this embodiment is substantially equivalent to that with respect to FIG. 7.
  • a concurrent advantage of the present invention is that the radially extending junctions 64 at the intersections of axially adjacent liner segments provide compatibility with often desirable adjunct cooling devices.
  • a perforated impingement cooling liner (not shown) can be bridged across adjacent junctions 64 to provide additional cooling.
  • the present invention has thus been illustrated to provide structure for substantial improvement in structural integrity of combustion chamber liners contemporaneously with maintaining or improving the formation of protective laminar film boundaries of cooling fluid. While the concepts of this invention have been illustrated with respect to several embodiments thereof, it is apparent that these concepts are subject to broad applicability and that numerous variations of the structure of the incorporated embodiments may be made by those skilled in the art without departing from the spirit of the presentinvention. For example, the relative dimensioning or disposition of the diffusion pockets may be varied depending upon flow rates and other variables. Furthermore, alternative means for diffusing flows and coalescing velocity profiles may be utilized to perform the same functions as herein described. Alternatively, the overhanging lip might be dispensed with, the exit from the pocket being designed to direct the flow against the liner. These and other variations are intended to be covered by the appended claims.
  • a cooling film promoter for passing, from a plenum containing cooling fluid flowing in a predetermined direction, a portion of the cooling fluid in a protective film upon a liner partially defining a hot gas passage, the promoter comprising:
  • a second liner segment partially defining the hot gas passage, the first and second liner segments cooperating to form a pocket, said second liner segment having a downstream end portion spaced from said first liner segment to form an exit from said pocket for directing cooling air along said first liner segment,
  • aperture means in said first liner segment for providing communication between the pocket and the plenum, wherein said aperture lS open to the direction generally opposite said predetermined direction within the plenum, whereby the cooling fluid entering the pocket is partially directed upstream with respect to the fluid flow in the plenum;
  • downstream end portion comprises a relatively short overhanging lip for directing cooling fluid from the pocket exit onto the first liner segment.
  • the pocket extends substantially circumferentially about the liner and the aperture means further includes a plurality of apertures spaced circumferentially relative to the liner for providing communication between the plenum and the pocket, and wherein said apertures are open to the direction generally opposite said predetermined direction within the plenum.
  • the pocket further comprises a closed end, and the apertures are disposed between a substantial portion of the pocket including said closed end, and said exit.
  • a second liner segment partially defining the hot gas passage, the first and second liner segments cooperating to form a pocket, said second liner segment having a downstream end portion spaced from said first liner segment to form an exit from said pocket for directing cooling air along said first liner segment means in said first liner segment for transferring cooling fluid from the plenum to the pocket;
  • said promoter is further characterized in that the pocket has a closed end, the exit opens in a direction parallel to the hot gas flow, the aperture is disposed upstream of both the closed end and the exit, and a baffle is disposed between the closed end and the exit about which the cool fluid is turned prior to reaching the exit.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00331519A 1973-02-12 1973-02-12 Cooling film promoter for combustion chambers Expired - Lifetime US3845620A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US00331519A US3845620A (en) 1973-02-12 1973-02-12 Cooling film promoter for combustion chambers
CA191,319A CA1004047A (en) 1973-02-12 1974-01-30 Cooling film promoter for combustion chambers
GB573474A GB1459500A (en) 1973-02-12 1974-02-07 Liners for disposition between a cooling fluid plenum and a hot gas passage
DE2406277A DE2406277C2 (de) 1973-02-12 1974-02-09 Kühllufteinlaß
IT20387/74A IT1006333B (it) 1973-02-12 1974-02-11 Favoritore di pellicola di raffed damento per camere di combustione
JP49017477A JPS5743813B2 (enrdf_load_stackoverflow) 1973-02-12 1974-02-12
BE140804A BE810902A (fr) 1973-02-12 1974-02-12 Dispositif de refroidissement de chambre de combustion
FR7404680A FR2217548B1 (enrdf_load_stackoverflow) 1973-02-12 1974-02-12

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00331519A US3845620A (en) 1973-02-12 1973-02-12 Cooling film promoter for combustion chambers

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US3845620A true US3845620A (en) 1974-11-05

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US00331519A Expired - Lifetime US3845620A (en) 1973-02-12 1973-02-12 Cooling film promoter for combustion chambers

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US (1) US3845620A (enrdf_load_stackoverflow)
JP (1) JPS5743813B2 (enrdf_load_stackoverflow)
BE (1) BE810902A (enrdf_load_stackoverflow)
CA (1) CA1004047A (enrdf_load_stackoverflow)
DE (1) DE2406277C2 (enrdf_load_stackoverflow)
FR (1) FR2217548B1 (enrdf_load_stackoverflow)
GB (1) GB1459500A (enrdf_load_stackoverflow)
IT (1) IT1006333B (enrdf_load_stackoverflow)

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3978662A (en) * 1975-04-28 1976-09-07 General Electric Company Cooling ring construction for combustion chambers
US3995422A (en) * 1975-05-21 1976-12-07 General Electric Company Combustor liner structure
US4184326A (en) * 1975-12-05 1980-01-22 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
US4232527A (en) * 1979-04-13 1980-11-11 General Motors Corporation Combustor liner joints
US4329848A (en) * 1979-03-01 1982-05-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Cooling of combustion chamber walls using a film of air
US4380906A (en) * 1981-01-22 1983-04-26 United Technologies Corporation Combustion liner cooling scheme
US4485630A (en) * 1982-12-08 1984-12-04 General Electric Company Combustor liner
US4566280A (en) * 1983-03-23 1986-01-28 Burr Donald N Gas turbine engine combustor splash ring construction
US4723413A (en) * 1985-11-19 1988-02-09 MTU Munuch, GmbH Reverse flow combustion chamber, especially reverse flow ring combustion chamber, for gas turbine propulsion units, with at least one flame tube wall film-cooling arrangement
US4896510A (en) * 1987-02-06 1990-01-30 General Electric Company Combustor liner cooling arrangement
US5363654A (en) * 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components
US5651662A (en) * 1992-10-29 1997-07-29 General Electric Company Film cooled wall
US5680767A (en) * 1995-09-11 1997-10-28 General Electric Company Regenerative combustor cooling in a gas turbine engine
US5826431A (en) * 1995-02-06 1998-10-27 Kabushiki Kaisha Toshiba Gas turbine multi-hole film cooled combustor liner and method of manufacture
US6554563B2 (en) * 2001-08-13 2003-04-29 General Electric Company Tangential flow baffle
US6675582B2 (en) * 2001-05-23 2004-01-13 General Electric Company Slot cooled combustor line
US20050050896A1 (en) * 2003-09-10 2005-03-10 Mcmasters Marie Ann Thick coated combustor liner
US20100092896A1 (en) * 2008-10-14 2010-04-15 General Electric Company Method and apparatus for introducing diluent flow into a combustor
US20150113994A1 (en) * 2013-03-12 2015-04-30 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US20160265366A1 (en) * 2013-11-11 2016-09-15 United Technologies Corporation Gas turbine engine turbine blade tip cooling
US20220307693A1 (en) * 2021-03-26 2022-09-29 Honda Motor Co., Ltd. Combustor for gas turbine engine
US20230003383A1 (en) * 2020-03-23 2023-01-05 Mitsubishi Heavy Industries, Ltd. Combustor and gas turbine provided with same
US11859824B2 (en) 2022-05-13 2024-01-02 General Electric Company Combustor with a dilution hole structure
US11859823B2 (en) 2022-05-13 2024-01-02 General Electric Company Combustor chamber mesh structure
US11867398B2 (en) 2022-05-13 2024-01-09 General Electric Company Hollow plank design and construction for combustor liner
US11994294B2 (en) 2022-05-13 2024-05-28 General Electric Company Combustor liner
US12066187B2 (en) 2022-05-13 2024-08-20 General Electric Company Plank hanger structure for durable combustor liner

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Publication number Priority date Publication date Assignee Title
US4050241A (en) * 1975-12-22 1977-09-27 General Electric Company Stabilizing dimple for combustion liner cooling slot
JPS6115418Y2 (enrdf_load_stackoverflow) * 1977-09-12 1986-05-13
FR2490728A1 (fr) * 1980-09-25 1982-03-26 Snecma Dispositif de refroidissement par film d'air pour tube a flamme de moteur a turbine a gaz
FR2604509B1 (fr) * 1986-09-25 1988-11-18 Snecma Procede de realisation d'un film de refroidissement pour chambre de combustion de turbomachine, film ainsi realise et chambre de combustion le comportant
JPH0182455U (enrdf_load_stackoverflow) * 1987-11-18 1989-06-01

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US2555965A (en) * 1950-03-24 1951-06-05 Gen Electric End cap for fluid fuel combustors
US2958194A (en) * 1951-09-24 1960-11-01 Power Jets Res & Dev Ltd Cooled flame tube
US3121996A (en) * 1961-10-02 1964-02-25 Lucas Industries Ltd Liquid fuel combustion apparatus
DE1270889B (de) * 1964-05-13 1968-06-20 Rolls Royce Kuehlvorrichtung fuer Brennkammern von Gasturbinentriebwerken
US3369363A (en) * 1966-01-19 1968-02-20 Gen Electric Integral spacing rings for annular combustion chambers
US3589127A (en) * 1969-02-04 1971-06-29 Gen Electric Combustion apparatus
US3589128A (en) * 1970-02-02 1971-06-29 Avco Corp Cooling arrangement for a reverse flow gas turbine combustor
US3738106A (en) * 1971-10-26 1973-06-12 Avco Corp Variable geometry combustors

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3978662A (en) * 1975-04-28 1976-09-07 General Electric Company Cooling ring construction for combustion chambers
US3995422A (en) * 1975-05-21 1976-12-07 General Electric Company Combustor liner structure
US4184326A (en) * 1975-12-05 1980-01-22 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
US4329848A (en) * 1979-03-01 1982-05-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Cooling of combustion chamber walls using a film of air
US4232527A (en) * 1979-04-13 1980-11-11 General Motors Corporation Combustor liner joints
US4380906A (en) * 1981-01-22 1983-04-26 United Technologies Corporation Combustion liner cooling scheme
US4485630A (en) * 1982-12-08 1984-12-04 General Electric Company Combustor liner
US4566280A (en) * 1983-03-23 1986-01-28 Burr Donald N Gas turbine engine combustor splash ring construction
US4723413A (en) * 1985-11-19 1988-02-09 MTU Munuch, GmbH Reverse flow combustion chamber, especially reverse flow ring combustion chamber, for gas turbine propulsion units, with at least one flame tube wall film-cooling arrangement
US4896510A (en) * 1987-02-06 1990-01-30 General Electric Company Combustor liner cooling arrangement
US5651662A (en) * 1992-10-29 1997-07-29 General Electric Company Film cooled wall
US5363654A (en) * 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components
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Also Published As

Publication number Publication date
BE810902A (fr) 1974-05-29
JPS5743813B2 (enrdf_load_stackoverflow) 1982-09-17
GB1459500A (en) 1976-12-22
FR2217548A1 (enrdf_load_stackoverflow) 1974-09-06
FR2217548B1 (enrdf_load_stackoverflow) 1980-11-21
DE2406277C2 (de) 1986-06-26
DE2406277A1 (de) 1974-08-15
IT1006333B (it) 1976-09-30
CA1004047A (en) 1977-01-25
JPS49112014A (enrdf_load_stackoverflow) 1974-10-25

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