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
Application number
GB02215/68A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of GB1187171A publication Critical patent/GB1187171A/en
Expired legal-status Critical Current

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.
GB02215/68A 1967-04-03 1968-03-13 Improvements in Fluid Impingement Starting Means for Gas Turbine Engines. Expired GB1187171A (en)

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)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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

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

Similar Documents

Publication Publication Date Title
GB1187171A (en) Improvements in Fluid Impingement Starting Means for Gas Turbine Engines.
GB1088360A (en) Improvements in gas turbine ducted fan engine sealing means
US4190397A (en) Windage shield
GB1113087A (en) Gas turbine power plant
US3703808A (en) Turbine blade tip cooling air expander
EP2055895A2 (en) Turbomachine rotor disk
GB1306575A (en) Segmented seal assembly for axial flow turbines
GB1493049A (en) Turbofan engine
GB1041587A (en) Improvements in gas turbine engines
GB1135349A (en) Stator assembly for a turbine or the like
GB790854A (en) Improvements in or relating to axial-flow fluid machines
GB758106A (en) Improvements in turbine nozzles
US3897168A (en) Turbomachine extraction flow guide vanes
GB758108A (en) Improvements in turbine nozzles
US3909155A (en) Sealing of vaned assemblies
GB1085349A (en) Improvements in or relating to rotor assemblies for turbines and like bladed machines
GB1535765A (en) Variable cycle turbofan engines
GB1197711A (en) Improvements in Turbofan Type Engine.
US3756740A (en) Turbine stage
GB1524956A (en) Gas tubine engine
GB1127660A (en) Gas turbine jet propulsion engine
GB1063359A (en) Jet propulsion engines
GB1256486A (en)
US3364678A (en) Means for stabilizing fluid flow in diffuser-combustor systems in axial flow gas turbine engines
GB1018168A (en) Improvements in stator assembly

Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees