IN2014DN03773A - - Google Patents
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- Publication number
- IN2014DN03773A IN2014DN03773A IN3773DEN2014A IN2014DN03773A IN 2014DN03773 A IN2014DN03773 A IN 2014DN03773A IN 3773DEN2014 A IN3773DEN2014 A IN 3773DEN2014A IN 2014DN03773 A IN2014DN03773 A IN 2014DN03773A
- Authority
- IN
- India
- Prior art keywords
- combustion chamber
- turbine
- contour
- conical contour
- thermal expansion
- Prior art date
Links
Classifications
-
- 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
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- 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
- F23R3/002—Wall structures
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00012—Details of sealing devices
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Abstract
A gas turbine (10) comprises a compressor (12), an annular combustion chamber (13), and a turbine (15), a combustion chamber shell (20a) of the combustion chamber (13) adjoining the turbine inlet (26) in a transition region (A) in order to introduce the hot gases generated in the combustion chamber (13) into the downstream turbine (15) such that a thermal expansion-induced relative movement between the combustion chamber (13) and the turbine inlet (26) is possible. Combustion chamber shell (20a) support elements (29) distributed on the periphery come into contact with a conical contour (31a) on the shaft cover (25) due to the thermal expansion (33) that occurs during operation and are supported on said contour. The aim of the invention is an improvement with respect to loading and service life. This is achieved in that the conical contour (31a) and the machine axis form an angle (a2) that allows the combustion chamber shell (20a) support elements (29) to slide onto the conical contour (31a) .
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP11186387 | 2011-10-24 | ||
PCT/EP2012/070930 WO2013060663A2 (en) | 2011-10-24 | 2012-10-23 | Gas turbine |
Publications (1)
Publication Number | Publication Date |
---|---|
IN2014DN03773A true IN2014DN03773A (en) | 2015-07-10 |
Family
ID=47045047
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
IN3773DEN2014 IN2014DN03773A (en) | 2011-10-24 | 2012-10-23 |
Country Status (7)
Country | Link |
---|---|
US (1) | US9708920B2 (en) |
EP (1) | EP2852735B1 (en) |
KR (1) | KR101613096B1 (en) |
CN (1) | CN104246373B (en) |
IN (1) | IN2014DN03773A (en) |
RU (1) | RU2597350C2 (en) |
WO (1) | WO2013060663A2 (en) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2637944T3 (en) * | 2014-06-06 | 2017-10-18 | MTU Aero Engines AG | Arrangement of the components of a gas turbine |
EP2998517B1 (en) * | 2014-09-16 | 2019-03-27 | Ansaldo Energia Switzerland AG | Sealing arrangement at the interface between a combustor and a turbine of a gas turbine and gas turbine with such a sealing arrangement |
EP3287610B1 (en) * | 2016-08-22 | 2019-07-10 | Ansaldo Energia Switzerland AG | Gas turbine transition duct |
US10697634B2 (en) | 2018-03-07 | 2020-06-30 | General Electric Company | Inner cooling shroud for transition zone of annular combustor liner |
US20220336123A1 (en) * | 2019-09-24 | 2022-10-20 | Ls Electric Co., Ltd. | Cooling apparatus for superconductor cooling container |
EP3835657A1 (en) * | 2019-12-10 | 2021-06-16 | Siemens Aktiengesellschaft | Combustion chamber with wall cooling |
CN112377946B (en) * | 2020-11-16 | 2022-02-11 | 四川航天中天动力装备有限责任公司 | Large bent pipe structure of axial floating type backflow annular combustion chamber |
Family Cites Families (38)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2592060A (en) * | 1946-03-25 | 1952-04-08 | Rolls Royce | Mounting of combustion chambers in jet-propulsion and gas-turbine power-units |
GB638807A (en) * | 1948-07-12 | 1950-06-14 | Havilland Engine Co Ltd | Improvements in or relating to gas turbines |
GB1010338A (en) * | 1962-09-11 | 1965-11-17 | Lucas Industries Ltd | Means for supporting the downstream end of a combustion chamber in a gas turbine engine |
DE1186275B (en) * | 1963-07-04 | 1965-01-28 | Daimler Benz Ag | Arrangement of the flame chamber of annular combustion chambers for gas turbine engines |
US3481146A (en) * | 1967-12-28 | 1969-12-02 | Lucas Industries Ltd | Combustion apparatus for gas turbine engines |
US3670467A (en) | 1970-04-27 | 1972-06-20 | Robert H Walker | Method and apparatus for manufacturing tumbling media |
US3670497A (en) * | 1970-09-02 | 1972-06-20 | United Aircraft Corp | Combustion chamber support |
US3928963A (en) * | 1974-11-04 | 1975-12-30 | Gen Motors Corp | Cast in place gas turbine containment ring and method of manufacture |
GB2102897B (en) * | 1981-07-27 | 1985-06-19 | Gen Electric | Annular seals |
US4821522A (en) * | 1987-07-02 | 1989-04-18 | United Technologies Corporation | Sealing and cooling arrangement for combustor vane interface |
FR2624953B1 (en) * | 1987-12-16 | 1990-04-20 | Snecma | COMBUSTION CHAMBER FOR TURBOMACHINES HAVING A DOUBLE WALL CONVERGENT |
US5271714A (en) * | 1992-07-09 | 1993-12-21 | General Electric Company | Turbine nozzle support arrangement |
US5265412A (en) * | 1992-07-28 | 1993-11-30 | General Electric Company | Self-accommodating brush seal for gas turbine combustor |
GB2328011A (en) * | 1997-08-05 | 1999-02-10 | Europ Gas Turbines Ltd | Combustor for gas or liquid fuelled turbine |
US6098397A (en) * | 1998-06-08 | 2000-08-08 | Caterpillar Inc. | Combustor for a low-emissions gas turbine engine |
JP2003527973A (en) * | 2000-03-22 | 2003-09-24 | シーメンス アクチエンゲゼルシヤフト | How to remove sealing means |
US6334310B1 (en) * | 2000-06-02 | 2002-01-01 | General Electric Company | Fracture resistant support structure for a hula seal in a turbine combustor and related method |
IT1317978B1 (en) * | 2000-06-16 | 2003-07-21 | Nuovo Pignone Spa | TRANSITION PIECE FOR COMBUSTION CHAMBERS OF NONANULAR GAS TURBINES. |
SE520594C2 (en) * | 2000-09-29 | 2003-07-29 | Turbec Ab | Burner chamber for a heat engine unit |
US6442946B1 (en) * | 2000-11-14 | 2002-09-03 | Power Systems Mfg., Llc | Three degrees of freedom aft mounting system for gas turbine transition duct |
US6450762B1 (en) * | 2001-01-31 | 2002-09-17 | General Electric Company | Integral aft seal for turbine applications |
US6860108B2 (en) * | 2003-01-22 | 2005-03-01 | Mitsubishi Heavy Industries, Ltd. | Gas turbine tail tube seal and gas turbine using the same |
US7152411B2 (en) * | 2003-06-27 | 2006-12-26 | General Electric Company | Rabbet mounted combuster |
US7178340B2 (en) * | 2003-09-24 | 2007-02-20 | Power Systems Mfg., Llc | Transition duct honeycomb seal |
US6997673B2 (en) * | 2003-12-11 | 2006-02-14 | Honeywell International, Inc. | Gas turbine high temperature turbine blade outer air seal assembly |
FR2871847B1 (en) * | 2004-06-17 | 2006-09-29 | Snecma Moteurs Sa | MOUNTING A TURBINE DISPENSER ON A COMBUSTION CHAMBER WITH CMC WALLS IN A GAS TURBINE |
WO2006059979A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Tip turbine engine integral case, vane, mount, and mixer |
US7082766B1 (en) * | 2005-03-02 | 2006-08-01 | General Electric Company | One-piece can combustor |
US7726114B2 (en) * | 2005-12-07 | 2010-06-01 | General Electric Company | Integrated combustor-heat exchanger and systems for power generation using the same |
US7604456B2 (en) * | 2006-04-11 | 2009-10-20 | Siemens Energy, Inc. | Vane shroud through-flow platform cover |
US7762766B2 (en) * | 2006-07-06 | 2010-07-27 | Siemens Energy, Inc. | Cantilevered framework support for turbine vane |
MY158901A (en) * | 2008-02-20 | 2016-11-30 | General Electric Technology Gmbh | Gas turbine having an annular combustion chamber |
AU2009216831B2 (en) * | 2008-02-20 | 2014-11-20 | General Electric Technology Gmbh | Gas turbine |
CN101965443B (en) * | 2008-02-27 | 2014-04-23 | 三菱重工业株式会社 | Gas turbine and method of opening chamber of gas turbine |
US8534076B2 (en) * | 2009-06-09 | 2013-09-17 | Honeywell Internationl Inc. | Combustor-turbine seal interface for gas turbine engine |
US8347636B2 (en) * | 2010-09-24 | 2013-01-08 | General Electric Company | Turbomachine including a ceramic matrix composite (CMC) bridge |
US20150167979A1 (en) * | 2013-12-17 | 2015-06-18 | General Electric Company | First stage nozzle or transition nozzle configured to promote mixing of respective combustion streams downstream thereof before entry into a first stage bucket of a turbine |
US10309652B2 (en) * | 2014-04-14 | 2019-06-04 | Siemens Energy, Inc. | Gas turbine engine combustor basket with inverted platefins |
-
2012
- 2012-10-23 EP EP12775033.9A patent/EP2852735B1/en active Active
- 2012-10-23 RU RU2014120759/06A patent/RU2597350C2/en active
- 2012-10-23 CN CN201280052419.0A patent/CN104246373B/en active Active
- 2012-10-23 WO PCT/EP2012/070930 patent/WO2013060663A2/en active Application Filing
- 2012-10-23 IN IN3773DEN2014 patent/IN2014DN03773A/en unknown
- 2012-10-23 KR KR1020147013476A patent/KR101613096B1/en active IP Right Grant
-
2014
- 2014-04-17 US US14/254,985 patent/US9708920B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
US20140223921A1 (en) | 2014-08-14 |
CN104246373B (en) | 2016-06-08 |
EP2852735A2 (en) | 2015-04-01 |
KR20140077978A (en) | 2014-06-24 |
US9708920B2 (en) | 2017-07-18 |
EP2852735B1 (en) | 2016-04-27 |
RU2014120759A (en) | 2015-12-10 |
RU2597350C2 (en) | 2016-09-10 |
WO2013060663A3 (en) | 2015-02-26 |
CN104246373A (en) | 2014-12-24 |
WO2013060663A2 (en) | 2013-05-02 |
KR101613096B1 (en) | 2016-04-20 |
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