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GB1353875A - Gas turbine ducted fan engines - Google Patents

Gas turbine ducted fan engines

Info

Publication number
GB1353875A
GB1353875A GB4284172A GB4284172A GB1353875A GB 1353875 A GB1353875 A GB 1353875A GB 4284172 A GB4284172 A GB 4284172A GB 4284172 A GB4284172 A GB 4284172A GB 1353875 A GB1353875 A GB 1353875A
Authority
GB
United Kingdom
Prior art keywords
shaft
compressor
secured
fan
turbine
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
GB4284172A
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of GB1353875A publication Critical patent/GB1353875A/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
    • 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
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1353875 Gas turbine ducted fan engines SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 15 Sept 1972 [16 Sept 1971] 42841/72 Headings F1G and F1J The invention relates to a gas turbine ducted fan engine in which a low pressure turbine drives the fan directly and the low pressure compressor through speed-increasing gearing. The engine shown in part only, comprises a fan 1, LP compressor 2 and HP compressor 3, the HP compressor being driven by an HP turbine (not shown) through shaft 5, and the LP compressor and the fan being driven by an LP turbine (not shown) through shaft 6. The fan rotor is keyed on the shaft 6 and is driven directly by the LP turbine. The LP compressor rotor 2a comprises a disc 10 to which is secured a member 11a forming the outer race of a bearing 11, the inner race of which is secured on the shaft 6; thus the LP compressor rotor is freely mounted on the shaft 6 and is driven therefrom by speed-increasing gearing 8 comprising a gear 16 secured on the shaft, and engaging a pinion 14 keyed to a layshaft 12; a second pinion 15 is keyed to the layshaft and engages a gear 17 formed on a ring member 17a secured to the compressor disc. The lay-shaft 12, which is one of a plurality spaced around the engine axis XX', is mounted in bearings 12a, 12b carried in a gear housing 9, 9c which is secured to stator structure 13 at 9a. The housing 9 carries a bearing 18 which rotatably supports the forward end of the shaft 6. Sealing devices are provided at 19, 20, 21.
GB4284172A 1971-09-16 1972-09-15 Gas turbine ducted fan engines Expired GB1353875A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7133402A FR2152466B1 (en) 1971-09-16 1971-09-16

Publications (1)

Publication Number Publication Date
GB1353875A true GB1353875A (en) 1974-05-22

Family

ID=9083053

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4284172A Expired GB1353875A (en) 1971-09-16 1972-09-15 Gas turbine ducted fan engines

Country Status (3)

Country Link
DE (1) DE2245478A1 (en)
FR (1) FR2152466B1 (en)
GB (1) GB1353875A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2012132469A (en) * 2006-10-31 2012-07-12 General Electric Co <Ge> Turbofan engine assembly
CN115653783A (en) * 2022-10-09 2023-01-31 中国航发湖南动力机械研究所 A fan turbine integrated structure and engine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3812027A1 (en) * 1988-04-11 1989-10-26 Mtu Muenchen Gmbh PROPFAN TURBO ENGINE
GB201903703D0 (en) * 2019-03-19 2019-05-01 Rolls Royce Plc A gas turbine engine bearing support structure

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2012132469A (en) * 2006-10-31 2012-07-12 General Electric Co <Ge> Turbofan engine assembly
CN115653783A (en) * 2022-10-09 2023-01-31 中国航发湖南动力机械研究所 A fan turbine integrated structure and engine

Also Published As

Publication number Publication date
DE2245478A1 (en) 1973-03-22
FR2152466B1 (en) 1974-03-29
FR2152466A1 (en) 1973-04-27

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Legal Events

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