US3797236A - Annular combustion chamber with ceramic annular ring - Google Patents

Annular combustion chamber with ceramic annular ring Download PDF

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Publication number
US3797236A
US3797236A US00261110A US3797236DA US3797236A US 3797236 A US3797236 A US 3797236A US 00261110 A US00261110 A US 00261110A US 3797236D A US3797236D A US 3797236DA US 3797236 A US3797236 A US 3797236A
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United States
Prior art keywords
annular
combustion chamber
face
gas turbine
turbine engine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US00261110A
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English (en)
Inventor
N Hooke
T Steel
J Bird
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Rolls Royce PLC
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Rolls Royce PLC
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Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
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Publication of US3797236A publication Critical patent/US3797236A/en
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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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • annular combustion chamber for a gas turbine engine comprises at least part of its annular wall made up of a ring of ceramic material, the ring being located by compression between a complete or interrupted annular frustoconical face and a second complete or interrupted annular face, which may be radial or frusto-conical.
  • the faces may comprise relieved portions which reduce heat conduction from the ceramic.
  • FIG. 1 is a partly broken away diagrammatic view of a gas turbine engine having a combustion chamber in accordance with the invention
  • FIG. 2 is an enlarged section through the combustion
  • an outer casing 16 and a compound inner casing 17 between which lies the combustion chamber proper This comprises an entry snout 18 through which primary air is fed to the combustion space, and the outer wall 19 and an inner wall 20 which between them define the combustion area.
  • These walls are made up of rings of metal welded together and are provided with holes for wall cooling air and discrete chutes for the ingress of primary and dilution air necessary for combustion. These walls are in accordance with the common Assignees US. Pat. application of Williamson Ser. No. 876,504 filed Nov. 13, 1969. Further discrete chutes provide dilution air which dilutes the hot gases. i
  • the flow area of the chamber is decreased before the gas flows through a row of nozzle guide vanes 21.
  • This reduction is mainly effected by the angular surfaceof the inner part 22 of the discharge nozzle. Since this surface effects a turning of the hot gases, it is one of the hottest areas of the combustion chamber. and therefore in the FIG. 2 embodiment the part 22 is made up of hot pressed silicon nitride.
  • the part 22 essentially comprises a frusto-conical ring whose inner periphery is formed as a substantially radial flange having a downstream facing radial surface 23 and an upstream facing frusto-conical surface 24.
  • the face 24 abuts against a corresponding frusto-conical surface 25 which is carried from part of the inner casing 17.
  • the face 25 is not completely annular but is relieved by radial slots.
  • the relieved face 25 is formed on a ring 26 which is carried by cylindrical extension 27 from a flange 28 bolted to the casing 17.
  • the extension 27 is ment between the hot ring 26 and the cooler flange 28.
  • a ring 29 having its surface 30 relieved as is the face 25 abuts against the face 23 and is urged against it by a corrugated or wave spring washer 31 which in turn bears against a flange 32 by way of an adjusting washer 33 and a static seal ring 34.
  • the flange 32 is bolted to the flange 28 and therefore the corrugated washer 31 urges the ring 29 towards the face 25 and traps the part'22 in position. Since the face 25 is frusto-conical the part 22 is not only located axially but is also given a radial location.
  • Flange 26 is cooled by air passing between its upstream surface and flange 38 on part 17. This air passes into the combustion chamber through holes 39 in part 26. Ring 29, wave washer 31 and adjacent parts are cooled by air passing through holes 40 in part 27 through wave washer 31 and thence into the combustion chamber outlet adjacent to the nozzle guide vane inner platform.
  • FIG. 3 there is shown an alternative embodiment in which the majority of the chamber is identical to the embodiment of FIG. 2, only the support structure for the part 22 being changed. Consequently only this part of the structure will be described.
  • the part 22 is provided with the radially extending inner flange on which is formed the face 24, and once again this abuts against the relieved face 25 on the ring 26 which is supported in an identical fashion to the FIG. 2 embodiment.
  • the face 23 is not used for location and instead an annular surface 41 is provided on the outer periphery of the part 22. This face bears against a corresponding relieved face 42 formed on an extension piece 43.
  • the extension piece has an inner portion 44 having an annular face similar to that of the part 29 in FIG. 2, and once again a corrugated washer 31 is provided which forces the part 44 and consequently the entire extension piece 43 toward the face 24.
  • the washer 31 is supported from the bolted flange 32 and the spacing washer 33 and static seal 34.
  • FIG. 3 the principle of the FIG. 3 embodiment is similar to that of the FIG. 2 embodiment, but in this case the part 22 is not cantilevered from its inner periphery but is supported over substantially its entire length which is clamped between the faces 41 and 24.
  • similar cooling flows of air to those of FIG. 2 may be provided.
  • a greater proportion of the combustion chamber is made up of silicon nitride.
  • the wall 19 and entry snout 18 of the combustion chamber are identical to those of the previous embodiments, but the wall comprises an upstream portion 45 which is made solely of metal parts as before and a downstream section 46 which is made up of an outer wall 47 of metal and an inner wall 61 of silicon nitride. It will be noted that outer and inner in this content mean with respect to the combustion space.
  • the outer wall 47 contains discrete chutes for the entry of primary and dilution air and is located at its downstream end by flange 60 to casing 17. This wall is load bearing and is used to support the inner silicon nitride wall.
  • the ring 50 has a substantially square downstream end which fits over a step 56 formed in the upstream surface of the inner part of the ring 51.
  • a substantially radial surface 57 is formed, and in a similar fashion to the FIG. 2 embodiment a ring 58 with slotted face is caused to press this face by the action of a corrugated spring washer 59.
  • the opposite face of the spring washer is connected to a bolted flange 60, the flange 60 forming part of a bolted up structure which also holds the outer skin 47 in place.
  • An annular combustion chamber for a gas turbine engine comprising at least one annular wall, an annular ring made of a ceramic material and forming at least a part of the axial length of said wall, support means for supporting said annular ceramic ring, said support means including a first annular frusto-conical face and an axially spaced second annular face opposing said first face and means to urge said first face and said second face towards one another, and said annular ceramic ring having a first frusto-conical face substantially complementary to and abutting said first face of said support means and a second face axially spaced from the first face of said ceramic ring and abutting and substantially complementary to said second face of said support means, said annular ceramic ring being supported under compression in a generally axial direction and being positioned both axially and radially by the urging together of said first face and said second face of said support means.
  • annular combustion chamberfor a gas turbine engine as claimed in claim 1 in which said second annular face of said annular ceramic ring lies substantially in a radial plane of said annular wall part.
  • annular combustion chamber for a gas turbine engine as claimed in claim 1 in which at least one of the respective abutting faces of said annular ceramic ring and said support means is relieved to reduce contact area between said annular ceramic ring and said support means to thereby reduce heat conduction from the annular ceramic ring.
  • An annular combustion chamber for a gas turbine engine as claimed in claim 1 in which said means to urge said first and second second faces of said support means together is a spring means.
  • An annular combustion chamber for a gas turbine 9 An annular combustion chamber for a gas turbine engine as claimed in claim 8 and in which said faces are formed on the first and last members of said plurality of rings whereby said plurality of rings are held together in compression.
  • annular combustion chamber for a gas turbine engine as claimed in claim 7 in which said faces of said support means engage with the respective faces of said annular ceramic ring defining said nozzle inner portion at substantially the same radius.
  • An annular combustion chamber for a gas turbine engine as claimed in claim 7 in which said faces of said support means respectively engage the faces of said annular ceramic ring of said nozzle inner portion at said rings inner and outer peripheries at different radii.
  • An annular combustion chamber for a gas turbine engine as claimed in claim 8 in which the intermediate members of the plurality of rings are retained together by abutting substantially complementary frusto-conical faces.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
US00261110A 1971-06-11 1972-06-08 Annular combustion chamber with ceramic annular ring Expired - Lifetime US3797236A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2747171 1971-06-11

Publications (1)

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US3797236A true US3797236A (en) 1974-03-19

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US00261110A Expired - Lifetime US3797236A (en) 1971-06-11 1972-06-08 Annular combustion chamber with ceramic annular ring

Country Status (4)

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US (1) US3797236A (Direct)
JP (1) JPS5334247B1 (Direct)
FR (1) FR2140625B1 (Direct)
IT (1) IT956447B (Direct)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3943703A (en) * 1973-05-22 1976-03-16 United Turbine AB and Co., Kommanditbolag Cooling passages through resilient clamping members in a gas turbine power plant
US5031399A (en) * 1989-07-24 1991-07-16 Sundstrand Corporation Turbine including a thermal growth accommodating mount for a vane assembly
US5280703A (en) * 1989-12-11 1994-01-25 Sundstrand Corporation Turbine nozzle cooling
US20070062202A1 (en) * 2005-09-16 2007-03-22 Pratt & Whitney Canada Corp. Cooled support boss for a combustor in a gas turbine engine
US20090060723A1 (en) * 2007-08-31 2009-03-05 Snecma separator for feeding cooling air to a turbine
US20120060503A1 (en) * 2010-09-08 2012-03-15 Alstom Technology Ltd Transitional region for a combustion chamber of a gas turbine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2548485A (en) * 1946-01-09 1951-04-10 Shell Dev Combustion chamber lining
US2710523A (en) * 1951-09-27 1955-06-14 A V Roe Canada Ltd Gas turbine tail cone
US2924537A (en) * 1957-07-22 1960-02-09 Martin Co Laminated thermal insulation
US3092962A (en) * 1960-03-16 1963-06-11 Thiokol Chemical Corp Casings for rocket motors

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3229464A (en) * 1962-01-15 1966-01-18 Bendix Corp Combustor comprising a flame tube and insulating means
GB1059199A (en) * 1965-10-20 1967-02-15 Rolls Royce Flame tube

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2548485A (en) * 1946-01-09 1951-04-10 Shell Dev Combustion chamber lining
US2710523A (en) * 1951-09-27 1955-06-14 A V Roe Canada Ltd Gas turbine tail cone
US2924537A (en) * 1957-07-22 1960-02-09 Martin Co Laminated thermal insulation
US3092962A (en) * 1960-03-16 1963-06-11 Thiokol Chemical Corp Casings for rocket motors

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3943703A (en) * 1973-05-22 1976-03-16 United Turbine AB and Co., Kommanditbolag Cooling passages through resilient clamping members in a gas turbine power plant
US5031399A (en) * 1989-07-24 1991-07-16 Sundstrand Corporation Turbine including a thermal growth accommodating mount for a vane assembly
US5280703A (en) * 1989-12-11 1994-01-25 Sundstrand Corporation Turbine nozzle cooling
US20070062202A1 (en) * 2005-09-16 2007-03-22 Pratt & Whitney Canada Corp. Cooled support boss for a combustor in a gas turbine engine
US7559203B2 (en) 2005-09-16 2009-07-14 Pratt & Whitney Canada Corp. Cooled support boss for a combustor in a gas turbine engine
US20090060723A1 (en) * 2007-08-31 2009-03-05 Snecma separator for feeding cooling air to a turbine
US8069669B2 (en) * 2007-08-31 2011-12-06 Snecma Separator for feeding cooling air to a turbine
US20120060503A1 (en) * 2010-09-08 2012-03-15 Alstom Technology Ltd Transitional region for a combustion chamber of a gas turbine
US9097118B2 (en) * 2010-09-08 2015-08-04 Alstom Technology Ltd. Transitional region for a combustion chamber of a gas turbine

Also Published As

Publication number Publication date
DE2227960A1 (de) 1973-01-04
IT956447B (it) 1973-10-10
DE2227960B2 (de) 1976-05-26
FR2140625B1 (Direct) 1977-12-23
FR2140625A1 (Direct) 1973-01-19
JPS5334247B1 (Direct) 1978-09-19

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