GB1454748A - Gas turbine ducted fan engines - Google Patents

Gas turbine ducted fan engines

Info

Publication number
GB1454748A
GB1454748A GB5290272A GB5290272A GB1454748A GB 1454748 A GB1454748 A GB 1454748A GB 5290272 A GB5290272 A GB 5290272A GB 5290272 A GB5290272 A GB 5290272A GB 1454748 A GB1454748 A GB 1454748A
Authority
GB
United Kingdom
Prior art keywords
fan
guide vanes
air
engine
inlet
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
GB5290272A
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.)
Hawker Siddeley Dynamics Ltd
Original Assignee
Hawker Siddeley Dynamics Ltd
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 Hawker Siddeley Dynamics Ltd filed Critical Hawker Siddeley Dynamics Ltd
Priority to GB5290272A priority Critical patent/GB1454748A/en
Priority to DE19732357420 priority patent/DE2357420A1/en
Priority to FR7340847A priority patent/FR2207246B1/fr
Publication of GB1454748A publication Critical patent/GB1454748A/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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/66—Reversing fan flow using reversing fan blades

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

1454748 Gas turbine ducted fan engines HAWKER SIDDELEY DYNAMICS Ltd 16 Nov 1973 [16 Nov 1972] 52902/72 Heading F1J The invention relates to a gas turbine ducted fan engine, the fan rotor of which has reversible pitch fan blades for use in aircraft braking, there being means for improving flow of air to the compressor of the core engine when the fan blades are operating in reverse pitch mode. The engine shown in Fig. 1b which is not in accordance with the invention comprises a fan rotor 11 disposed with a fan casing 16, there being stator guide vanes 14 disposed within the fan duct downstream of the fan rotor blades. The inlet 12 to the compressor of the core engine is shown and comprises inlet guide vanes 17. The engine is shown operating in reverse thrust mode in which air is flowing forwardly through the fan to discharge through the normal inlet, some of the air reversing as indicated at 20 to flow through the inlet guide vane assembly 17 to the compressor of the core engine. The swirl imparted to the inflowing air by the guide vanes 14 results in incorrect entry to the guide vanes 17 with consequent inefficient swirling as indicated at 21. In accordance with the invention flow correcting guide vanes 22 are disposed around the intake lip of the core engine and are so inclined as to remove the swirl imparted to the inflowing air by the stator guide vanes 14. The guide vanes 22 prevent a substantially zero incidence angle to the air-flow through the fan duct when the fan rotor blades are in normal forward pitch. As shown the guide vanes 22 are extensions of the inlet guide vanes 17, extending around the intake lip and rearwardly along the outer wall of the intake.
GB5290272A 1972-11-16 1972-11-16 Gas turbine ducted fan engines Expired GB1454748A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB5290272A GB1454748A (en) 1972-11-16 1972-11-16 Gas turbine ducted fan engines
DE19732357420 DE2357420A1 (en) 1972-11-16 1973-11-14 GAS TURBINE ENGINE SYSTEM
FR7340847A FR2207246B1 (en) 1972-11-16 1973-11-16

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5290272A GB1454748A (en) 1972-11-16 1972-11-16 Gas turbine ducted fan engines

Publications (1)

Publication Number Publication Date
GB1454748A true GB1454748A (en) 1976-11-03

Family

ID=10465758

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5290272A Expired GB1454748A (en) 1972-11-16 1972-11-16 Gas turbine ducted fan engines

Country Status (3)

Country Link
DE (1) DE2357420A1 (en)
FR (1) FR2207246B1 (en)
GB (1) GB1454748A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111980804A (en) * 2020-08-24 2020-11-24 广州沐风信息科技有限公司 Gas turbine power generation equipment
US11396888B1 (en) 2017-11-09 2022-07-26 Williams International Co., L.L.C. System and method for guiding compressible gas flowing through a duct

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3135758A1 (en) * 2022-05-20 2023-11-24 Safran Aircraft Engines Retention casing of a fan having a truncated spherical part

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1518513A (en) * 1967-04-12 1968-03-22 Dowty Rotol Ltd Gas turbine engine machines
FR1518518A (en) * 1967-04-12 1968-03-22 Dowty Rotol Ltd Improvements to gas turbines

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11396888B1 (en) 2017-11-09 2022-07-26 Williams International Co., L.L.C. System and method for guiding compressible gas flowing through a duct
CN111980804A (en) * 2020-08-24 2020-11-24 广州沐风信息科技有限公司 Gas turbine power generation equipment
CN111980804B (en) * 2020-08-24 2021-11-16 盐城市钊扬工业设计有限公司 Gas turbine power generation equipment

Also Published As

Publication number Publication date
FR2207246B1 (en) 1977-03-11
FR2207246A1 (en) 1974-06-14
DE2357420A1 (en) 1974-05-22

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Legal Events

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