GB1161186A - A Gas Turbine Ducted Fan Engine. - Google Patents

A Gas Turbine Ducted Fan Engine.

Info

Publication number
GB1161186A
GB1161186A GB25484/68A GB2548468A GB1161186A GB 1161186 A GB1161186 A GB 1161186A GB 25484/68 A GB25484/68 A GB 25484/68A GB 2548468 A GB2548468 A GB 2548468A GB 1161186 A GB1161186 A GB 1161186A
Authority
GB
United Kingdom
Prior art keywords
casing
wall
members
welded
fan
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
GB25484/68A
Inventor
James Oswald Mortlock
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 GB25484/68A priority Critical patent/GB1161186A/en
Priority to FR6915489A priority patent/FR2014140A1/fr
Priority to US825308A priority patent/US3566606A/en
Priority to DE1926432A priority patent/DE1926432C3/en
Publication of GB1161186A publication Critical patent/GB1161186A/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
    • 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
    • F02C7/047—Heating to prevent icing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

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

1,161,186. Gas turbine jet propulion plant; axial flow fans. ROLLS-ROYCE Ltd. May 28, 1968, No.25484/68. Headings F1C, F1G and F1J. In a gas turbine ducted fan engine having a front fan surrounded by an annular casing at least a portion 22 of the casing is formed by two spaced apart walls 20, 24, the latter wall consisting of members 25 each having an integral flange 28 extending to the wall 20 and secured thereto, e.g. by welding. Circumferentially adjacent members 25 overlap at recesses 27 and are welded together. The flanges 28 define axially extending cavities 23. The portion 22 forms part of the radially inner wall of the annular fan casing (16) upstream of the tips of the fan blades (17, Fig. 1, not shown), the outer wall of the casing being formed by a wall 21 welded to the portion 22 via annular members 33, 34 and brackets 35. In operation, hot de-icing air supplied to the downstream end of the casing passes through apertures 36, 37 in the members 33, 34 to impinge on the leading edge of the casing. The hot air then flows through the cavities 23 and into the fan duct via a passage 41 between the portion 22 and a frusto-conical member 40. In a modification, Fig. 4 (not shown), the flange 28 on each member 25 is U-shaped and, as well as being welded to the wall 20 (at 43), has a foot (44) welded to the adjacent member 25.
GB25484/68A 1968-05-28 1968-05-28 A Gas Turbine Ducted Fan Engine. Expired GB1161186A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB25484/68A GB1161186A (en) 1968-05-28 1968-05-28 A Gas Turbine Ducted Fan Engine.
FR6915489A FR2014140A1 (en) 1968-05-28 1969-05-13
US825308A US3566606A (en) 1968-05-28 1969-05-16 Gas turbine ducted fan engine
DE1926432A DE1926432C3 (en) 1968-05-28 1969-05-23 Gas turbine engine with a fan rotating in an annular duct

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB25484/68A GB1161186A (en) 1968-05-28 1968-05-28 A Gas Turbine Ducted Fan Engine.

Publications (1)

Publication Number Publication Date
GB1161186A true GB1161186A (en) 1969-08-13

Family

ID=10228454

Family Applications (1)

Application Number Title Priority Date Filing Date
GB25484/68A Expired GB1161186A (en) 1968-05-28 1968-05-28 A Gas Turbine Ducted Fan Engine.

Country Status (4)

Country Link
US (1) US3566606A (en)
DE (1) DE1926432C3 (en)
FR (1) FR2014140A1 (en)
GB (1) GB1161186A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0357173A1 (en) * 1988-08-24 1990-03-07 General Motors Corporation Inlet particle separator de-icing system

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3933327A (en) * 1974-08-30 1976-01-20 Rohr Industries, Inc. Aircraft anti-icing plenum
US4471609A (en) * 1982-08-23 1984-09-18 The Boeing Company Apparatus and method for minimizing engine backbone bending
US5088277A (en) * 1988-10-03 1992-02-18 General Electric Company Aircraft engine inlet cowl anti-icing system
JP4791691B2 (en) * 2001-06-06 2011-10-12 ハウデン・パワー・アクティーゼルスカブ Gas outlet unit for large blower assembly
GB0211800D0 (en) * 2002-05-22 2002-07-03 Short Brothers Plc An ice protection system for aircraft structures
GB2416192B (en) * 2004-07-14 2006-09-27 Rolls Royce Plc Ducted fan with containment structure
US8657567B2 (en) * 2007-05-29 2014-02-25 United Technologies Corporation Nacelle compartment plenum for bleed air flow delivery system
US8206102B2 (en) * 2007-08-16 2012-06-26 United Technologies Corporation Attachment interface for a gas turbine engine composite duct structure
FR2941675B1 (en) * 2009-02-02 2012-08-17 Airbus France AIRCRAFT NACELLE COMPRISING AN OPTIMIZED ACOUSTIC TREATMENT SYSTEM.
EP2391542B1 (en) 2009-02-02 2014-07-30 Airbus Operations (S.A.S.) Engine nacelle having a noise reducing structure
US9534505B2 (en) * 2012-07-23 2017-01-03 United Technologies Corporation Integrated nacelle inlet and metallic fan containment case
FR3075759B1 (en) * 2017-12-21 2020-11-06 Airbus Operations Sas ANTERIOR NACELLE PART OF AN AIRCRAFT PROPELLER ASSEMBLY CONTAINING A SHOCK ABSORBER ELEMENT

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0357173A1 (en) * 1988-08-24 1990-03-07 General Motors Corporation Inlet particle separator de-icing system

Also Published As

Publication number Publication date
DE1926432B2 (en) 1974-01-03
DE1926432A1 (en) 1970-04-02
DE1926432C3 (en) 1974-07-25
US3566606A (en) 1971-03-02
FR2014140A1 (en) 1970-04-17

Similar Documents

Publication Publication Date Title
US2856755A (en) Combustion chamber with diverse combustion and diluent air paths
US2625793A (en) Gas turbine apparatus with air-cooling means
US3433020A (en) Gas turbine engine rotors
US3374624A (en) Gas turbine engine combustion equipment
GB1088360A (en) Improvements in gas turbine ducted fan engine sealing means
GB1161186A (en) A Gas Turbine Ducted Fan Engine.
GB1113087A (en) Gas turbine power plant
GB1008526A (en) Axial flow bladed rotor, e.g. for a turbine
US3300121A (en) Axial-flow compressor
GB1079195A (en) Gas turbine engine cooling
US2526281A (en) Turbine and turbine nozzle construction
GB1195012A (en) Rotor for Bladed Fluid Flow Machines.
JP2009047411A (en) Turbo machine diffuser
GB904138A (en) Improvements in or relating to stator structures, for example for axial flow gas turbine engines
GB1034260A (en) Aerofoil-shaped blade for use in a fluid flow machine
GB1251312A (en)
GB1195973A (en) Air Intakes.
GB1197711A (en) Improvements in Turbofan Type Engine.
US5085039A (en) Coanda phenomena combustor for a turbine engine
GB1284858A (en) Gas turbine engine constructions
US2459850A (en) Turbine apparatus
GB712523A (en) Improvements in or relating to guide vane assemblies in annular fluid ducts
GB981857A (en) Gas turbine engine
GB960812A (en) Compressor for a gas turbine engine
GB787666A (en) Improvements in blades for gas turbine engines

Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLE Entries relating assignments, transmissions, licences in the register of patents
PLE Entries relating assignments, transmissions, licences in the register of patents
PCNP Patent ceased through non-payment of renewal fee