GB1203712A - Improvements in or relating to gas turbine engine - Google Patents

Improvements in or relating to gas turbine engine

Info

Publication number
GB1203712A
GB1203712A GB5448968A GB5448968A GB1203712A GB 1203712 A GB1203712 A GB 1203712A GB 5448968 A GB5448968 A GB 5448968A GB 5448968 A GB5448968 A GB 5448968A GB 1203712 A GB1203712 A GB 1203712A
Authority
GB
United Kingdom
Prior art keywords
turbine
fan
duct
disposed
compressor
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
GB5448968A
Inventor
Geoffrey Light Wilde
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 US795269*A priority Critical patent/US3534556A/en
Priority to FR6902544A priority patent/FR2001451A1/fr
Priority to DE19691905692 priority patent/DE1905692A1/en
Publication of GB1203712A publication Critical patent/GB1203712A/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
    • F02K3/065—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 and aft fans

Abstract

1,203,712. Gas turbine ducted fan engines. ROLLS-ROYCE Ltd. Feb.4, 1969 [Feb.7, 1968; Nov. 16, 1968], Nos. 5981/68 and 54489/68. Heading F1J. A gas turbine ducted fan engine comprises independently rotatable IP and HP compressors, combustion equipment, and HP and IP turbines drivingly inter-connected with the respective compressors, a single-stage front fan and a singlestage rear fan, the compressors, combustion equipment and turbines being located within an inner flow duct and the fans being disposed within a fan duct and being driven by a turbine of the engine. The engine shown in Fig. 1 comprises an IP compressor 10, HP compressor 12, combustion equipment 14, HP turbine 16, IP turbine 20 and LP turbine 18 all disposed in flow series in an inner main flow duct, the HP turbine driving the HP compressor through shaft 26 and the IP turbine driving the IP compressor through shaft 22. The LP turbine 18 drives a front fan 28 through shaft 30 also a rear fan 38 which is mounted radially outwardly of the turbine blades. The front and rear fans are disposed within a fan duct 32 which is supported from the casing of the main flow duct by guide vanes 36, 40 which vanes are disposed sufficiently downstream of the associated fan blades 28, 38 to ensure that rotor wakes are dispersed before the air flows through the guide vanes. A portion of air from the front fan passes into the main flow duct. In Fig. the engine comprises IP compressor 114, HP compressor 115, combustion equipment 116, HP turbine 117, IP turbine 118 and an LP turbine which is in the form of two separate turbines 119, 120. The first LP turbine 119 drives a front fan 113 through shaft 121 and the second LP turbine 120 drives a rear fan 125 through a driving connection 124 at the tips of the turbine blades. The front and rear fans 113, 125 are disposed within a fan duct 112 and stator guide vanes 127 are disposed downstream of the rear fan 125. A series of helical vanes 126 are disposed within the fan duct so that the air-flow from the front fan has some whirl when it enters the rear fan. The fan duct may be made as a monocoque structure which may be connected direct to aircraft structure, vanes 126 carrying loads from the main casing. Variable inlet nozzle guide vanes may be provided at the inlet to the LP turbine.
GB5448968A 1968-02-07 1968-02-07 Improvements in or relating to gas turbine engine Expired GB1203712A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US795269*A US3534556A (en) 1968-02-07 1969-01-30 Gas turbine engine
FR6902544A FR2001451A1 (en) 1968-02-07 1969-02-05
DE19691905692 DE1905692A1 (en) 1968-02-07 1969-02-05 Gas turbine jet engine with bypass fan

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB598168 1968-02-07

Publications (1)

Publication Number Publication Date
GB1203712A true GB1203712A (en) 1970-09-03

Family

ID=9806223

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5448968A Expired GB1203712A (en) 1968-02-07 1968-02-07 Improvements in or relating to gas turbine engine

Country Status (1)

Country Link
GB (1) GB1203712A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2174762B (en) * 1985-05-01 1990-04-04 Gen Electric Counter rotation power turbine
CN115405421A (en) * 2022-11-01 2022-11-29 北京航空航天大学 Three-rotor variable-cycle engine overall structure with interstage combustion chamber

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2174762B (en) * 1985-05-01 1990-04-04 Gen Electric Counter rotation power turbine
CN115405421A (en) * 2022-11-01 2022-11-29 北京航空航天大学 Three-rotor variable-cycle engine overall structure with interstage combustion chamber
CN115405421B (en) * 2022-11-01 2023-02-03 北京航空航天大学 Three-rotor variable-cycle engine overall structure with interstage combustion chamber

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Legal Events

Date Code Title Description
PS Patent sealed
PLE Entries relating assignments, transmissions, licences in the register of patents
PLNP Patent lapsed through nonpayment of renewal fees