WO2004023038A1 - Stress relief feature for aerated gas turbine fuel injector - Google Patents
Stress relief feature for aerated gas turbine fuel injector Download PDFInfo
- Publication number
- WO2004023038A1 WO2004023038A1 PCT/CA2003/001254 CA0301254W WO2004023038A1 WO 2004023038 A1 WO2004023038 A1 WO 2004023038A1 CA 0301254 W CA0301254 W CA 0301254W WO 2004023038 A1 WO2004023038 A1 WO 2004023038A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- stress
- relief
- slit
- nozzle
- air passages
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
- F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
- F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
-
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2211/00—Thermal dilatation prevention or compensation
-
- 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
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
Definitions
- the present invention generally relates to gas turbine engines, and more particularly, to the relief of thermal stresses in an aerodynamic surface of a gas turbine engine.
- the present invention is particularly suited for relieving thermal stress in a fuel nozzle of a gas turbine engine combustor.
- aerated fuel nozzles for atomizing fuel in a combustion chamber of a gas turbine engine.
- Such nozzles generally comprise a tubular cylindrical head or outer air swirler defining an array of circumferentially spaced-apart air passages to pass pressurized compressor discharged air at elevated temperatures into the combustion chamber of the engine to atomize the fuel film exiting from the tip of the spray nozzle.
- a fuel nozzle for a combustor in a gas turbine engine comprises a fuel nozzle body having a fuel inlet port at one end and a spray tip at the other end for atomizing the fuel.
- the spray tip includes a nozzle head defining a plurality of air passages for conveying hot pressurized air into the combustor. Each pair of adjacent air passages defines a web.
- the nozzle head has at least one stress-relief slit which extends through one of the air passages for reducing thermally induced stresses in the webs during operation.
- the stress-relief slit is sized to substantially prevent air leakage from the air passage.
- a method for reducing thermal stresses in a gas turbine engine fuel nozzle of the type having a nozzle head defining an array of air passages comprising the steps of: selecting at least one of the air passages, and defining a stress-relief slit through each selected air passage.
- a method for improving the fatigue life of a gas turbine engine part having an aerodynamic surface defining a fluid flow path comprising the steps of: identifying a first location on said aerodynamic surface which is prone to cracking due to thermal stress, relieving stress from said first location by forming an appropriate number of stress-relief slits in said aerodynamic surface at a second location remote from said first location, said stress-relief slits being sized to substantially prevent fluid leakage from said fluid flow path through said stress-relief slits.
- FIG. 1 is a simplified axial cross-section of the combustor of a gas turbine engine which includes the present invention.
- FIG. 2 is an enlarged perspective view of a fuel nozzle incorporating the features of the present invention
- FIG. 3 is a fragmentary, enlarged cross-sectional, axial view of the fuel nozzle shown in Fig. 2;
- Fig. 4 is a rear elevation of the nozzle head of the fuel nozzle shown in Fig. 2;
- Fig. 5 is a cross-section taken along line 5-5 in Fig. 4.
- FIG. 1 shows a combustor section 10 which includes an annular casing 12 and an annular combustor tube 14 concentric with a turbine section 16.
- the turbine section 16 is shown with a typical rotor 18 having blades 19 and a stator vane 20 upstream from the blades 19.
- FIG. 1 An airblast fuel injector or nozzle 22 is shown in Fig. 1 as being located at the end of the annular combustor tube 14 and directed axially thereof.
- the nozzle 22 is mounted to the casing 12 by means of a bracket 30.
- the nozzle is mounted to the casing 12 by means of a bracket 30.
- nozzle 22 includes a fitting 31 to be connected to a typical fuel line. There may be several fuel nozzles 22 located on the wall 28 of the combustion chamber, and they may be circumferentially spaced-apart.
- the fuel nozzle 22 includes a stem 24 surrounded by a shield 32.
- the fuel injector 22 also includes a spray tip 26 which is mounted to the combustion chamber wall 28 for spraying or atomizing fuel into the combustion chamber. Only the front face of the tip 26 extends within the combustion chamber while most of the tip 26 is located in the air passage outside wall 28. [00021] As shown in Fig. 3, the spray tip 26 includes a machined body 34.
- An axial recess in the body 34 defines a primary fuel chamber 36.
- An insert 50 provided within the recess defines the nozzle opening 44 communicating with the fuel chamber 36 for passing the primary fuel.
- a valving device 38 includes a spiral vane which causes the primary fuel to swirl within the chamber 36.
- the stem 46 of the valving device 38 acts as metering valve for the primary fuel as it exits through the nozzle opening 44.
- a shield 42 is fitted onto the insert 50.
- a second annular insert 51 is mounted to the body 34 concentrically of the insert 50 and forms part of the secondary fuel distribution gallery and nozzle.
- the secondary fuel passes through somewhat spiral passages making up the fuel gallery 48.
- the secondary fuel is eventually delivered to an annular fuel nozzle opening 54 which is also a swirler to provide the swirl to the secondary fuel.
- the fuel nozzle opening 54 is formed by the insert 51 and a cylindrical tubular head 55 or outer swirler which fits onto the tip body 34 and is concentric with the inserts 50 and 51. As shown in Figs. 2 to 4, the head 55 defines a row of circumferentially spaced-apart air passages 62, which are adapted to convey pressurized hot air for blending with the primary and secondary fuel sprays issuing from the nozzle openings 44 and 54. [00023] In operation, the air flowing through the air passages 62 can reach up to 1000° F, whereas the temperature of the fuel flowing through the nozzle opening 54 is less than 200° F. This results in severe thermal stresses on the leading edge of the webs 64 between the air passages 62.
- the gradient of temperature existing across the head 55 is known as the primary source of low cycle fatigue cracking of the head 55.
- the crack propagation will normally take place at the thinnest portion of the webs 64.
- each slit 68 is preferably provided in the form of a straight cut through a selected air passage.
- Each slit 68 extends through the full thickness of the flanged portion of the head 55 and along the length of the associated air passage (see Fig. 5).
- the slits 68 can extend radially inwardly in the tubular head 55 or be oriented at any arbitrary angle with respect thereto, as long as the slit 68 intersects the selected air passages.
- One advantage of the present invention resides in the fact that it can be applied to new components as well as existing components. Indeed, the stress-relief slits 68 can be formed in the nozzle head at the manufacturing stage thereof or even in an existing nozzle head which already presents some cracking. The addition of stress relief slits to a cracked piece will not repair the cracks but will significantly delay the propagation thereof to an unacceptable level. [00026]
- the present invention is particularly interesting as a recondition technique in that it can be retrofitted to an existing nozzle part with minimal cost while extending its service life by a factor of 2 to 3 times.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Spray-Type Burners (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP03793514A EP1540247B1 (en) | 2002-09-03 | 2003-08-22 | Stress relief feature for aerated gas turbine fuel injector |
CA2496908A CA2496908C (en) | 2002-09-03 | 2003-08-22 | Stress relief feature for aerated gas turbine fuel injector |
DE60332465T DE60332465D1 (en) | 2002-09-03 | 2003-08-22 | AFTSTOFFEINSPRITZDÜSE |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/232,397 | 2002-09-03 | ||
US10/232,397 US6823677B2 (en) | 2002-09-03 | 2002-09-03 | Stress relief feature for aerated gas turbine fuel injector |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2004023038A1 true WO2004023038A1 (en) | 2004-03-18 |
Family
ID=31976995
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/CA2003/001254 WO2004023038A1 (en) | 2002-09-03 | 2003-08-22 | Stress relief feature for aerated gas turbine fuel injector |
Country Status (5)
Country | Link |
---|---|
US (1) | US6823677B2 (en) |
EP (1) | EP1540247B1 (en) |
CA (1) | CA2496908C (en) |
DE (1) | DE60332465D1 (en) |
WO (1) | WO2004023038A1 (en) |
Families Citing this family (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6883332B2 (en) * | 1999-05-07 | 2005-04-26 | Parker-Hannifin Corporation | Fuel nozzle for turbine combustion engines having aerodynamic turning vanes |
US7117678B2 (en) * | 2004-04-02 | 2006-10-10 | Pratt & Whitney Canada Corp. | Fuel injector head |
US8348180B2 (en) * | 2004-06-09 | 2013-01-08 | Delavan Inc | Conical swirler for fuel injectors and combustor domes and methods of manufacturing the same |
US7533531B2 (en) * | 2005-04-01 | 2009-05-19 | Pratt & Whitney Canada Corp. | Internal fuel manifold with airblast nozzles |
US7559202B2 (en) * | 2005-11-15 | 2009-07-14 | Pratt & Whitney Canada Corp. | Reduced thermal stress fuel nozzle assembly |
US8015815B2 (en) * | 2007-04-18 | 2011-09-13 | Parker-Hannifin Corporation | Fuel injector nozzles, with labyrinth grooves, for gas turbine engines |
US20090320483A1 (en) * | 2008-06-26 | 2009-12-31 | General Electric Company | Variable Orifice Plug for Turbine Fuel Nozzle |
US20100162714A1 (en) * | 2008-12-31 | 2010-07-01 | Edward Claude Rice | Fuel nozzle with swirler vanes |
US8096757B2 (en) * | 2009-01-02 | 2012-01-17 | General Electric Company | Methods and apparatus for reducing nozzle stress |
EP2236934A1 (en) * | 2009-03-18 | 2010-10-06 | Siemens Aktiengesellschaft | Burner assembly |
US8555649B2 (en) * | 2009-09-02 | 2013-10-15 | Pratt & Whitney Canada Corp. | Fuel nozzle swirler assembly |
GB0918099D0 (en) * | 2009-10-16 | 2009-12-02 | Rolls Royce Plc | Fuel injector mounting system |
GB0918169D0 (en) * | 2009-10-19 | 2009-12-02 | Rolls Royce Plc | Fuel injector mounting system |
EP2327933A1 (en) | 2009-11-30 | 2011-06-01 | Siemens Aktiengesellschaft | Burner assembly |
US10317081B2 (en) | 2011-01-26 | 2019-06-11 | United Technologies Corporation | Fuel injector assembly |
US8794544B2 (en) * | 2011-06-06 | 2014-08-05 | General Electric Company | Combustor nozzle and method for modifying the combustor nozzle |
US9052113B1 (en) | 2011-06-06 | 2015-06-09 | General Electric Company | Combustor nozzle and method for modifying the combustor nozzle |
US9777637B2 (en) | 2012-03-08 | 2017-10-03 | General Electric Company | Gas turbine fuel flow measurement using inert gas |
US9447974B2 (en) | 2012-09-13 | 2016-09-20 | United Technologies Corporation | Light weight swirler for gas turbine engine combustor and a method for lightening a swirler for a gas turbine engine |
US9400104B2 (en) | 2012-09-28 | 2016-07-26 | United Technologies Corporation | Flow modifier for combustor fuel nozzle tip |
JP6018714B2 (en) * | 2012-11-21 | 2016-11-02 | ゼネラル・エレクトリック・カンパニイ | Anti-coking liquid fuel cartridge |
GB201303428D0 (en) | 2013-02-27 | 2013-04-10 | Rolls Royce Plc | A vane structure and a method of manufacturing a vane structure |
WO2014197072A2 (en) * | 2013-03-15 | 2014-12-11 | United Technologies Corporation | Fuel nozzle for a gas turbine engine |
US9556795B2 (en) * | 2013-09-06 | 2017-01-31 | Delavan Inc | Integrated heat shield |
US10400672B2 (en) * | 2013-11-04 | 2019-09-03 | United Technologies Corporation | Cooled fuel injector system for a gas turbine engine |
US10557630B1 (en) | 2019-01-15 | 2020-02-11 | Delavan Inc. | Stackable air swirlers |
DE102019103640A1 (en) * | 2019-02-13 | 2020-08-13 | Mitsubishi Hitachi Power Systems Europe Gmbh | Fuel nozzle with expansion slots for a pulverized coal burner |
US11060460B1 (en) | 2019-04-01 | 2021-07-13 | Marine Turbine Technologies, LLC | Fuel distribution system for gas turbine engine |
EP3748231B1 (en) * | 2019-06-05 | 2023-08-30 | Siemens Energy Global GmbH & Co. KG | Burner and burner tip |
US11639795B2 (en) | 2021-05-14 | 2023-05-02 | Pratt & Whitney Canada Corp. | Tapered fuel gallery for a fuel nozzle |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3064425A (en) * | 1959-10-05 | 1962-11-20 | Gen Motors Corp | Combustion liner |
EP0552477A1 (en) * | 1992-01-21 | 1993-07-28 | Westinghouse Electric Corporation | Gas turbine dual fuel nozzle |
WO1999061838A1 (en) * | 1998-05-22 | 1999-12-02 | Pratt & Whitney Canada Corp. | Gas turbine fuel injector |
US6149075A (en) * | 1999-09-07 | 2000-11-21 | General Electric Company | Methods and apparatus for shielding heat from a fuel nozzle stem of fuel nozzle |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2959355A (en) * | 1958-07-25 | 1960-11-08 | Sandberg Serrell Corp | Nozzle |
US3692372A (en) | 1971-06-24 | 1972-09-19 | Gen Electric | Thermally expansible bearing assembly |
US4536932A (en) | 1982-11-22 | 1985-08-27 | United Technologies Corporation | Method for eliminating low cycle fatigue cracking in integrally bladed disks |
US5255508A (en) | 1991-11-01 | 1993-10-26 | United Technologies Corporation | Fuel nozzle assembly and method for making the assembly |
US5535585A (en) | 1994-12-13 | 1996-07-16 | Eichhorn; Gunther | Slotted exhaust liner |
JP3710099B2 (en) * | 1995-03-31 | 2005-10-26 | 株式会社アイ・エイチ・アイ・エアロスペース | Jetta Beta |
US6289676B1 (en) * | 1998-06-26 | 2001-09-18 | Pratt & Whitney Canada Corp. | Simplex and duplex injector having primary and secondary annular lud channels and primary and secondary lud nozzles |
-
2002
- 2002-09-03 US US10/232,397 patent/US6823677B2/en not_active Expired - Lifetime
-
2003
- 2003-08-22 DE DE60332465T patent/DE60332465D1/en not_active Expired - Lifetime
- 2003-08-22 CA CA2496908A patent/CA2496908C/en not_active Expired - Lifetime
- 2003-08-22 WO PCT/CA2003/001254 patent/WO2004023038A1/en not_active Application Discontinuation
- 2003-08-22 EP EP03793514A patent/EP1540247B1/en not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3064425A (en) * | 1959-10-05 | 1962-11-20 | Gen Motors Corp | Combustion liner |
EP0552477A1 (en) * | 1992-01-21 | 1993-07-28 | Westinghouse Electric Corporation | Gas turbine dual fuel nozzle |
WO1999061838A1 (en) * | 1998-05-22 | 1999-12-02 | Pratt & Whitney Canada Corp. | Gas turbine fuel injector |
US6149075A (en) * | 1999-09-07 | 2000-11-21 | General Electric Company | Methods and apparatus for shielding heat from a fuel nozzle stem of fuel nozzle |
Also Published As
Publication number | Publication date |
---|---|
CA2496908A1 (en) | 2004-03-18 |
CA2496908C (en) | 2011-03-22 |
EP1540247A1 (en) | 2005-06-15 |
US6823677B2 (en) | 2004-11-30 |
DE60332465D1 (en) | 2010-06-17 |
EP1540247B1 (en) | 2010-05-05 |
US20040040310A1 (en) | 2004-03-04 |
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