GB2164706B - Pressurized nacelle compartment for active clearance controlled gas turbine engines - Google Patents

Pressurized nacelle compartment for active clearance controlled gas turbine engines

Info

Publication number
GB2164706B
GB2164706B GB08424149A GB8424149A GB2164706B GB 2164706 B GB2164706 B GB 2164706B GB 08424149 A GB08424149 A GB 08424149A GB 8424149 A GB8424149 A GB 8424149A GB 2164706 B GB2164706 B GB 2164706B
Authority
GB
United Kingdom
Prior art keywords
pressurized
gas turbine
turbine engines
controlled gas
active clearance
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
GB08424149A
Other versions
GB2164706A (en
GB8424149D0 (en
Inventor
John Pentti Nikkanen
James Gerard Griffin
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Priority to GB08424149A priority Critical patent/GB2164706B/en
Priority to FR8415389A priority patent/FR2571433B1/en
Priority to DE19843437076 priority patent/DE3437076A1/en
Publication of GB8424149D0 publication Critical patent/GB8424149D0/en
Publication of GB2164706A publication Critical patent/GB2164706A/en
Application granted granted Critical
Publication of GB2164706B publication Critical patent/GB2164706B/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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
GB08424149A 1984-09-25 1984-09-25 Pressurized nacelle compartment for active clearance controlled gas turbine engines Expired GB2164706B (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB08424149A GB2164706B (en) 1984-09-25 1984-09-25 Pressurized nacelle compartment for active clearance controlled gas turbine engines
FR8415389A FR2571433B1 (en) 1984-09-25 1984-10-08 PRESSURE BLADE FOR GAS TURBINE ENGINES WITH CONTROLLED ACTIVE SPACE
DE19843437076 DE3437076A1 (en) 1984-09-25 1984-10-09 PRESSURIZED GONDOLA CHAMBER FOR GAS TURBINE ENGINES WITH ACTIVE CLEARANCE CONTROL

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB08424149A GB2164706B (en) 1984-09-25 1984-09-25 Pressurized nacelle compartment for active clearance controlled gas turbine engines

Publications (3)

Publication Number Publication Date
GB8424149D0 GB8424149D0 (en) 1984-10-31
GB2164706A GB2164706A (en) 1986-03-26
GB2164706B true GB2164706B (en) 1988-06-08

Family

ID=10567203

Family Applications (1)

Application Number Title Priority Date Filing Date
GB08424149A Expired GB2164706B (en) 1984-09-25 1984-09-25 Pressurized nacelle compartment for active clearance controlled gas turbine engines

Country Status (3)

Country Link
DE (1) DE3437076A1 (en)
FR (1) FR2571433B1 (en)
GB (1) GB2164706B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11746726B2 (en) 2020-05-05 2023-09-05 Rohr, Inc. Aircraft propulsion system nozzle with internal flow passage

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5284012A (en) * 1991-05-16 1994-02-08 General Electric Company Nacelle cooling and ventilation system
FR2697289B1 (en) * 1992-10-28 1994-12-09 Snecma Double-flow turbojet with air heating system on the primary nozzle.
EP0794118B1 (en) * 1996-03-04 2002-09-18 The Boeing Company Flow control apparatus for gas turbine engine installation pressure relief doors
CN1078663C (en) * 1996-08-22 2002-01-30 波音公司 Flow control apparatus for gas turbine engine installation pressure relief doors
US6651929B2 (en) 2001-10-29 2003-11-25 Pratt & Whitney Canada Corp. Passive cooling system for auxiliary power unit installation
DE102009010647A1 (en) * 2009-02-26 2010-09-02 Rolls-Royce Deutschland Ltd & Co Kg Running column adjustment system of an aircraft gas turbine
DE102011106961A1 (en) * 2011-07-08 2013-01-10 Rolls-Royce Deutschland Ltd & Co Kg Flight gas turbine engine i.e. turbomachine, has flow guide element designed as radiator element, and core thruster surrounded by by-pass channel, where partial flow is conducted from channel through engine casing for cooling core thruster
DE102017117291A1 (en) * 2017-07-31 2019-01-31 Rolls-Royce Deutschland Ltd & Co Kg Air guiding device in an aircraft engine
FR3072360A1 (en) * 2017-10-17 2019-04-19 Airbus Operations LANDING TRAIN CASE ROOF FOR AIRCRAFT COMPRISING AN INCLINED REAR PANEL

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2853854A (en) * 1957-02-04 1958-09-30 Orenda Engines Ltd Shroud assembly for gas turbine engines
US4069662A (en) * 1975-12-05 1978-01-24 United Technologies Corporation Clearance control for gas turbine engine
US4163366A (en) * 1977-05-23 1979-08-07 Avco Corporation Apparatus for disposal of leaking fluids in a turbofan engine
US4304093A (en) * 1979-08-31 1981-12-08 General Electric Company Variable clearance control for a gas turbine engine
US4474001A (en) * 1981-04-01 1984-10-02 United Technologies Corporation Cooling system for the electrical generator of a turbofan gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11746726B2 (en) 2020-05-05 2023-09-05 Rohr, Inc. Aircraft propulsion system nozzle with internal flow passage

Also Published As

Publication number Publication date
DE3437076A1 (en) 1986-04-10
FR2571433A1 (en) 1986-04-11
FR2571433B1 (en) 1986-12-26
GB2164706A (en) 1986-03-26
GB8424149D0 (en) 1984-10-31

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Legal Events

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

Effective date: 20000925