GB1417154A - Compressor intakes - Google Patents

Compressor intakes

Info

Publication number
GB1417154A
GB1417154A GB5067772A GB5067772A GB1417154A GB 1417154 A GB1417154 A GB 1417154A GB 5067772 A GB5067772 A GB 5067772A GB 5067772 A GB5067772 A GB 5067772A GB 1417154 A GB1417154 A GB 1417154A
Authority
GB
United Kingdom
Prior art keywords
compressor
opening
gas turbine
air intake
stator blades
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
GB5067772A
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB5067772A priority Critical patent/GB1417154A/en
Publication of GB1417154A publication Critical patent/GB1417154A/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
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1417154 Gas turbine ducted fan engine: compressor air intake ROLLS-ROYCE (1971) Ltd 18 Oct 1973 [3 Nov 1972] 50677/72 Headings F1C, F1G and F1J The compressor air intake 16, for a ducted fan gas turbine, includes an annular opening 38 in the compressor casing, and a splitter ring 44 adjacent the opening deflecting air into the opening but allowing debris to pass on out of a rear nozzle (22), Fig. 1 (not shown). The splitter ring is supported by a row of stator blades 50, struts 54, and stator blades 56.
GB5067772A 1972-11-03 1972-11-03 Compressor intakes Expired GB1417154A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB5067772A GB1417154A (en) 1972-11-03 1972-11-03 Compressor intakes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5067772A GB1417154A (en) 1972-11-03 1972-11-03 Compressor intakes

Publications (1)

Publication Number Publication Date
GB1417154A true GB1417154A (en) 1975-12-10

Family

ID=10456904

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5067772A Expired GB1417154A (en) 1972-11-03 1972-11-03 Compressor intakes

Country Status (1)

Country Link
GB (1) GB1417154A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4928480A (en) * 1988-03-04 1990-05-29 General Electric Company Separator having multiple particle extraction passageways
GB2243190A (en) * 1990-03-19 1991-10-23 Gen Electric Ejecting foreign matter from the primary flow path of a gas turbine engine
EP0517461A1 (en) * 1991-06-04 1992-12-09 General Electric Company Aircraft gas turbine engine particle separator
GB2298458A (en) * 1995-03-02 1996-09-04 Lucas Aerospace Power Equip Cooling electromechanical apparatus
US9890711B2 (en) 2010-09-21 2018-02-13 United Technologies Corporation Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4928480A (en) * 1988-03-04 1990-05-29 General Electric Company Separator having multiple particle extraction passageways
GB2243190A (en) * 1990-03-19 1991-10-23 Gen Electric Ejecting foreign matter from the primary flow path of a gas turbine engine
US5123240A (en) * 1990-03-19 1992-06-23 General Electric Co. Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine
GB2243190B (en) * 1990-03-19 1994-04-13 Gen Electric Apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine.
EP0517461A1 (en) * 1991-06-04 1992-12-09 General Electric Company Aircraft gas turbine engine particle separator
US5201801A (en) * 1991-06-04 1993-04-13 General Electric Company Aircraft gas turbine engine particle separator
GB2298458A (en) * 1995-03-02 1996-09-04 Lucas Aerospace Power Equip Cooling electromechanical apparatus
US5731644A (en) * 1995-03-02 1998-03-24 Lucas Aerospace Power Equipment Corporation Integral cooling air diffuser for electromechanical apparatus
GB2298458B (en) * 1995-03-02 1999-01-06 Lucas Aerospace Power Equip Integral cooling air diffuser for electromechanical apparatus
US9890711B2 (en) 2010-09-21 2018-02-13 United Technologies Corporation Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events

Similar Documents

Publication Publication Date Title
GB1328993A (en) Air intakes for gas turbine engines
GB1171966A (en) Improvements in or relating to Multiple Flow Gas Turbine Jet Engines
GB1113542A (en) Gas turbine engine
GB1151177A (en) Improvements in and relating to Gas Turbine Engines
GB1085619A (en) Gas turbine engine
GB588096A (en) Improvements in or relating to internal combustion turbine power plants
GB1513338A (en) Rotor blade for a gas turbine engine
GB925010A (en) Improvements in or relating to turbo-fan units
GB1417154A (en) Compressor intakes
GB1197711A (en) Improvements in Turbofan Type Engine.
GB1257497A (en)
GB1450133A (en) Cooling of gas turbine engines
GB838602A (en) Improvements in or relating to gas turbine plant
GB1452267A (en) Jet propulsion powerplant frames
GB981857A (en) Gas turbine engine
GB1514096A (en) Axial flow rotor or stator assembly
GB1032274A (en) Mounting of ducted fan turbine engines in the tail of an aircraft
GB1041048A (en) Improvements in aircraft having jet-propulsion power-plants
GB1190364A (en) Gas Turbine Engines
GB793823A (en) Helicopters
GB1003639A (en) Improvements relating to gas turbine engines
GB1223999A (en) Gas turbine engine
GB789800A (en) Jet propelled aircraft
GB1507914A (en) Device for preventing foreign matters from being sucked into a gas turbine engine for an aircraft
GB1535598A (en) Turbofan aero engines and propulsion nozzles therefor

Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee