GB1344305A - Gas turbine engines - Google Patents

Gas turbine engines

Info

Publication number
GB1344305A
GB1344305A GB1344305DA GB1344305A GB 1344305 A GB1344305 A GB 1344305A GB 1344305D A GB1344305D A GB 1344305DA GB 1344305 A GB1344305 A GB 1344305A
Authority
GB
United Kingdom
Prior art keywords
shaft
duct
openings
valve member
module
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
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
Publication of GB1344305A publication Critical patent/GB1344305A/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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants

Abstract

1344305 Gas turbine engines - fan module ROLLS-ROYCE (1971) Ltd 4 Nov 1971 51250/71 Heading F1G The invention relates to a detachable fan module to which a gas turbine engine may be secured, the module comprising in flow series an air inlet 12, a single stage fan 14 mounted on a rotatable shaft 22, at least one row of outlet guide vanes 16, a diffuser duct 18 and at least one row of compressor inlet guide vanes 20. The shaft 22 is supported in bearings 24 in a structure 26 and is connected at its forward end through a ratchet device 32 to a starter motor shaft 28; the shaft 22 is connected at its rearward end through an intermediate shaft 42 to the shaft 46 of the low pressure compressor of the engine 11. The diffuser duct 18 is defined by mutually divergent walls 60, 62 which may move axially with respect to the other parts of the module. The compressor inlet guide vanes 20 are mounted in shroud members 58, 70 which are in sealed engagement with the duct walls 60, 62. Openings 76 provided in the outer wall 62 of the duct are associated with a valve member in the form of a flexible tube 80 whereby the openings may be open (broken line position of the valve member) or closed (full line position of the valve member); the purpose of the openings is to allow excess pressure to be vented. The object of the invention is to permit power of an engine to be increased by "supercharging" the compressor.
GB1344305D 1971-11-04 1971-11-04 Gas turbine engines Expired GB1344305A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5125071 1971-11-04

Publications (1)

Publication Number Publication Date
GB1344305A true GB1344305A (en) 1974-01-23

Family

ID=10459251

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1344305D Expired GB1344305A (en) 1971-11-04 1971-11-04 Gas turbine engines

Country Status (1)

Country Link
GB (1) GB1344305A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0298014A1 (en) * 1987-06-29 1989-01-04 United Technologies Corporation Engine modularity
CN104160116A (en) * 2012-03-07 2014-11-19 三菱日立电力系统株式会社 Sealing device and gas turbine having the same

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0298014A1 (en) * 1987-06-29 1989-01-04 United Technologies Corporation Engine modularity
CN104160116A (en) * 2012-03-07 2014-11-19 三菱日立电力系统株式会社 Sealing device and gas turbine having the same
CN104160116B (en) * 2012-03-07 2015-12-02 三菱日立电力系统株式会社 Seal arrangement and possess the gas turbine of seal arrangement
US9206705B2 (en) 2012-03-07 2015-12-08 Mitsubishi Hitachi Power Systems, Ltd. Sealing device and gas turbine having the same

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees