GB1187171A - Improvements in Fluid Impingement Starting Means for Gas Turbine Engines. - Google Patents
Improvements in Fluid Impingement Starting Means for Gas Turbine Engines.Info
- Publication number
- GB1187171A GB1187171A GB02215/68A GB1221568A GB1187171A GB 1187171 A GB1187171 A GB 1187171A GB 02215/68 A GB02215/68 A GB 02215/68A GB 1221568 A GB1221568 A GB 1221568A GB 1187171 A GB1187171 A GB 1187171A
- Authority
- GB
- United Kingdom
- Prior art keywords
- ring
- flange
- nozzle
- ring member
- stator
- 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
Links
Classifications
-
- 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
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
- F02C7/27—Fluid drives
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)
Abstract
1,187,171. Gas turbine engines - starting. GENERAL ELECTRIC CO. March 13, 1968 [April 3, 1967], No. 12215/68. Heading F1G. The invention relates to a fluid impingement type starting system for a gas turbine engine, the starting system comprising a nozzle ring which is located downstream of a ring of turbine stator blades and upstream of a ring of turbine rotor blades, there being nozzle outlets in the nozzle ring through which starting fluid is directed on to the turbine rotor blades. The engine shown comprises a two stage turbine 12 comprising second stage nozzle guide vanes 18 and second stage rotor blades 13 which are mounted on the rotor 14. A starter nozzle ring 22 is located between the stator blade assembly 18 and the rotor blade assembly, 13, the ring 22 being of channel section and being formed in its base portion 24 with nozzle outlets 21 through which starting fluid may be discharged on to the rotor blades 13 to start the engine. The turbine stator structure comprises parts 2, 3, 4 secured together, the part 3 being formed with a starting fluid inlet duct 15 also with a duct part 17 through which starting fluid can pass to the nozzle ring member 22. The ring member 22 is supported in a "floating" manner as follows: the upstream flange 32 of the member bears against a radially inwardly projecting flange 27 of the stator member 3, while the downstream flange 33 of the ring member bears against a flange of the ring member 28 which is itself secured between the stator members 3, 4, the flange of the ring member 28 carrying projecting pins 29 which engage within radial slots 30 formed in the downstream flange 33 of the ring member 22 is located with provision for thermal radial expansion. The stator members 2, 3, 4 are onepiece, undivided members which allow the starter ring member to be assembled in an axial manner.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US62800567A | 1967-04-03 | 1967-04-03 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1187171A true GB1187171A (en) | 1970-04-08 |
Family
ID=24517022
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB02215/68A Expired GB1187171A (en) | 1967-04-03 | 1968-03-13 | Improvements in Fluid Impingement Starting Means for Gas Turbine Engines. |
Country Status (5)
Country | Link |
---|---|
US (1) | US3451215A (en) |
BE (1) | BE712412A (en) |
DE (1) | DE1626036A1 (en) |
FR (1) | FR1563248A (en) |
GB (1) | GB1187171A (en) |
Families Citing this family (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3742705A (en) * | 1970-12-28 | 1973-07-03 | United Aircraft Corp | Thermal response shroud for rotating body |
US3748056A (en) * | 1971-02-09 | 1973-07-24 | Nissan Motor | Turbine blade cooling |
US3730640A (en) * | 1971-06-28 | 1973-05-01 | United Aircraft Corp | Seal ring for gas turbine |
FR2185753B1 (en) * | 1972-05-26 | 1976-06-11 | Szydlowski Joseph | |
US3901622A (en) * | 1973-05-31 | 1975-08-26 | Gen Motors Corp | Yieldable shroud support |
US3864056A (en) * | 1973-07-27 | 1975-02-04 | Westinghouse Electric Corp | Cooled turbine blade ring assembly |
US4092824A (en) * | 1974-05-28 | 1978-06-06 | Vereinigte Flugtechnische Werke-Fokker Gmbh | Method of operating a turbine |
US3924581A (en) * | 1974-12-06 | 1975-12-09 | Curtiss Wright Corp | Doweling construction for rotary engine housing |
US4161102A (en) * | 1977-10-05 | 1979-07-17 | Teledyne Industries, Inc. | Turbine engine starting system |
US4268221A (en) * | 1979-03-28 | 1981-05-19 | United Technologies Corporation | Compressor structure adapted for active clearance control |
US5463864A (en) * | 1993-12-27 | 1995-11-07 | United Technologies Corporation | Fuel nozzle guide for a gas turbine engine combustor |
DE19520100A1 (en) * | 1995-06-01 | 1996-12-05 | Jean Kuhn | Rotational explosion engine |
US6032457A (en) * | 1996-06-27 | 2000-03-07 | United Technologies Corporation | Fuel nozzle guide |
US5916142A (en) * | 1996-10-21 | 1999-06-29 | General Electric Company | Self-aligning swirler with ball joint |
US6644033B2 (en) * | 2002-01-17 | 2003-11-11 | The Boeing Company | Tip impingement turbine air starter for turbine engine |
WO2006112807A2 (en) * | 2004-12-01 | 2006-10-26 | United Technologies Corporation | Turbine engine and method for starting a turbine engine |
US7871248B2 (en) * | 2007-02-20 | 2011-01-18 | Honeywell International Inc. | Airframe mounted electric motor driven lubrication pump control deoil system |
US8490408B2 (en) * | 2009-07-24 | 2013-07-23 | Pratt & Whitney Canada Copr. | Continuous slot in shroud |
EP2733314B1 (en) * | 2012-11-15 | 2017-04-05 | Safran Aero Boosters SA | Radial attachment and positioning flanges for axial turbomachine casing sections |
US11073044B2 (en) * | 2013-01-21 | 2021-07-27 | Raytheon Technologies Corporation | Adjustable floating oil channel for gas turbine engine gear drive |
FR3063313B1 (en) * | 2017-02-28 | 2022-10-28 | Safran Aircraft Engines | AIRCRAFT ENGINE INPUT ARRANGEMENT INCLUDING A MECHANICAL DECOUPLER |
US11085309B2 (en) | 2017-09-22 | 2021-08-10 | General Electric Company | Outer drum rotor assembly |
US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
CN114151228B (en) * | 2022-02-09 | 2022-04-22 | 中国航发四川燃气涡轮研究院 | Method for dividing binary vector spray pipe regulating sheet into discrete cold air areas |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2457833A (en) * | 1943-02-03 | 1949-01-04 | Westinghouse Electric Corp | Cartridge starter for combustion gas turbines |
US2959919A (en) * | 1958-01-02 | 1960-11-15 | Gen Electric | Gas impingement starter nozzle for turbines |
US2971333A (en) * | 1958-05-14 | 1961-02-14 | Gen Electric | Adjustable gas impingement turbine nozzles |
US3009320A (en) * | 1959-06-15 | 1961-11-21 | Gen Electric | Fluid impingement starter for turbine engines |
US3085396A (en) * | 1959-07-03 | 1963-04-16 | Rolls Royce | Gas turbine engine with gas starter |
GB1069199A (en) * | 1965-02-20 | 1967-05-17 | Bristol Siddeley Engines Ltd | Improvements in means for starting gas turbine engines |
-
1967
- 1967-04-03 US US628005A patent/US3451215A/en not_active Expired - Lifetime
-
1968
- 1968-03-12 DE DE19681626036 patent/DE1626036A1/en active Pending
- 1968-03-13 GB GB02215/68A patent/GB1187171A/en not_active Expired
- 1968-03-15 FR FR1563248D patent/FR1563248A/fr not_active Expired
- 1968-03-19 BE BE712412D patent/BE712412A/xx unknown
Also Published As
Publication number | Publication date |
---|---|
DE1626036A1 (en) | 1971-03-04 |
BE712412A (en) | 1968-07-31 |
FR1563248A (en) | 1969-04-11 |
US3451215A (en) | 1969-06-24 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PLNP | Patent lapsed through nonpayment of renewal fees |