EP2541147A3 - System and method for adaptive impingement cooling - Google Patents

System and method for adaptive impingement cooling Download PDF

Info

Publication number
EP2541147A3
EP2541147A3 EP12174426.2A EP12174426A EP2541147A3 EP 2541147 A3 EP2541147 A3 EP 2541147A3 EP 12174426 A EP12174426 A EP 12174426A EP 2541147 A3 EP2541147 A3 EP 2541147A3
Authority
EP
European Patent Office
Prior art keywords
liner
support
mounting support
adaptive
spacer
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.)
Withdrawn
Application number
EP12174426.2A
Other languages
German (de)
French (fr)
Other versions
EP2541147A2 (en
Inventor
James A. Dierberger
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
Publication of EP2541147A2 publication Critical patent/EP2541147A2/en
Publication of EP2541147A3 publication Critical patent/EP2541147A3/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

An adaptive cooling structure comprises a mounting support 44, a liner 42, and a spacer 66. The mounting support 44 has a coolant aperture 62 for directing cooling air AC through the support 44. The liner 42 has a first surface 52 facing away from the mounting support 44 and a second surface 54 facing towards the support 44. The liner 42 is coupled to the mounting support 44, and the spacer 66 is positioned between the support 44 and the liner 42. The positioning of the spacer 66 creates a chamber 70 between the mounting support 44 and the liner 42, thus allowing the cooling air AC to impinge on the second surface 54 of the liner 42. The liner wall 48 is configured to deflect away from the mounting support 44 to expand the chamber 70, thus allowing the cooling air AC to further impinge on the second surface 54 of the liner 42.
EP12174426.2A 2011-06-30 2012-06-29 System and method for adaptive impingement cooling Withdrawn EP2541147A3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/174,166 US20130000309A1 (en) 2011-06-30 2011-06-30 System and method for adaptive impingement cooling

Publications (2)

Publication Number Publication Date
EP2541147A2 EP2541147A2 (en) 2013-01-02
EP2541147A3 true EP2541147A3 (en) 2017-11-01

Family

ID=46456392

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12174426.2A Withdrawn EP2541147A3 (en) 2011-06-30 2012-06-29 System and method for adaptive impingement cooling

Country Status (2)

Country Link
US (1) US20130000309A1 (en)
EP (1) EP2541147A3 (en)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9341118B2 (en) * 2009-12-29 2016-05-17 Rolls-Royce Corporation Various layered gas turbine engine component constructions
US9247672B2 (en) * 2013-01-21 2016-01-26 Parker-Hannifin Corporation Passively controlled smart microjet cooling array
WO2014123850A1 (en) * 2013-02-06 2014-08-14 United Technologies Corporation Gas turbine engine component with upstream-directed cooling film holes
EP2954261B1 (en) 2013-02-08 2020-03-04 United Technologies Corporation Gas turbine engine combustor
US10077681B2 (en) 2013-02-14 2018-09-18 United Technologies Corporation Compliant heat shield liner hanger assembly for gas turbine engines
EP3055530B1 (en) * 2013-10-07 2020-08-12 United Technologies Corporation Bonded combustor wall for a turbine engine
EP3058201B1 (en) * 2013-10-18 2018-07-18 United Technologies Corporation Combustor wall having cooling element(s) within a cooling cavity
US10386066B2 (en) * 2013-11-22 2019-08-20 United Technologies Corpoation Turbine engine multi-walled structure with cooling element(s)
WO2015084444A1 (en) 2013-12-06 2015-06-11 United Technologies Corporation Gas turbine engine wall assembly interface
EP3099976B1 (en) * 2014-01-30 2019-03-13 United Technologies Corporation Cooling flow for leading panel in a gas turbine engine combustor
US10935241B2 (en) * 2014-05-09 2021-03-02 Raytheon Technologies Corporation Additively manufactured hotspot portion of a turbine engine component having heat resistant properties and method of manufacture
CN107076416B (en) 2014-08-26 2020-05-19 西门子能源公司 Film cooling hole arrangement for acoustic resonator in gas turbine engine
US10132498B2 (en) * 2015-01-20 2018-11-20 United Technologies Corporation Thermal barrier coating of a combustor dilution hole
EP3269932A1 (en) * 2016-07-13 2018-01-17 MTU Aero Engines GmbH Shrouded gas turbine blade
DE102016222099A1 (en) * 2016-11-10 2018-05-17 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber of a gas turbine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5131222A (en) * 1990-11-28 1992-07-21 The United States Of Americas As Represented By The Secretary Of The Air Force Thermally valved cooling system for exhaust nozzle systems
US5209059A (en) * 1991-12-27 1993-05-11 The United States Of America As Represented By The Secretary Of The Air Force Active cooling apparatus for afterburners
US20040211188A1 (en) * 2003-04-28 2004-10-28 Hisham Alkabie Noise reducing combustor
US20100077764A1 (en) * 2008-10-01 2010-04-01 United Technologies Corporation Structures with adaptive cooling
US20110011095A1 (en) * 2009-07-17 2011-01-20 Ladd Scott A Washer with cooling passage for a turbine engine combustor

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7140185B2 (en) * 2004-07-12 2006-11-28 United Technologies Corporation Heatshielded article

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5131222A (en) * 1990-11-28 1992-07-21 The United States Of Americas As Represented By The Secretary Of The Air Force Thermally valved cooling system for exhaust nozzle systems
US5209059A (en) * 1991-12-27 1993-05-11 The United States Of America As Represented By The Secretary Of The Air Force Active cooling apparatus for afterburners
US20040211188A1 (en) * 2003-04-28 2004-10-28 Hisham Alkabie Noise reducing combustor
US20100077764A1 (en) * 2008-10-01 2010-04-01 United Technologies Corporation Structures with adaptive cooling
US20110011095A1 (en) * 2009-07-17 2011-01-20 Ladd Scott A Washer with cooling passage for a turbine engine combustor

Also Published As

Publication number Publication date
EP2541147A2 (en) 2013-01-02
US20130000309A1 (en) 2013-01-03

Similar Documents

Publication Publication Date Title
EP2541147A3 (en) System and method for adaptive impingement cooling
EP2354660A3 (en) Combustor liner segment seal member
EP2290196A3 (en) Adjustable fan case liner and mounting method
EP2549188A3 (en) Insert for a gas turbine engine combustor
WO2013163150A8 (en) Turbine airfoil with local wall thickness control
WO2014042857A3 (en) Metallic sandwich structure having small bend radius
EP2538026A3 (en) Cooling system for turbine airfoil including ice-cream-cone-shaped pedestals
WO2010062428A3 (en) Integrated service tube and impingement baffle for a gas turbine engine
EP2369135A3 (en) Blade outer air seal for a gas turbine engine and corresponding gas turbine engine
EP3926157A4 (en) Cooling system for aircraft gas turbine engine
EP2623727A3 (en) Turbofan engine fan case cartridge, corresponding fixture and method of manufacturing
EP2562354A3 (en) Cooling insert for a gas turbine engine airfoil
EP2551592A3 (en) Microcircuit cooling for gas turbine engine combustor
EP2101041A3 (en) Cooling air manifold splash plate for a gas turbine engine
EP2574845A3 (en) Combustion system and method of assembling the same
EP2434105A3 (en) Metallic backing for composite flange of a fan containment case
EP3225790A3 (en) Turbine engine cleaning systems and methods
WO2007130576A3 (en) System and method for improved field of view x-ray imaging using a non-stationary anode
EP3556999B8 (en) Double wall airfoil cooling configuration for gas turbine engine
EP2172708A3 (en) Structures with adaptive cooling
WO2015147929A3 (en) Cooling an aperture body of a combustor wall
EP2374997A3 (en) Cooling circuit of a gas turbine engine
EP2363644A3 (en) Hybrid venturi cooling system
EP2434107A3 (en) Anti-fret liner assembly for a turbine engine
EP2613036A3 (en) Gas turbine inlet system

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: UNITED TECHNOLOGIES CORPORATION

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/00 20060101AFI20170926BHEP

Ipc: F23R 3/04 20060101ALI20170926BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20180501

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20180919

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20190130