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WO2015050592A3 - Gas turbine engine combustor liner panel - Google Patents

Gas turbine engine combustor liner panel Download PDF

Info

Publication number
WO2015050592A3
WO2015050592A3 PCT/US2014/042130 US2014042130W WO2015050592A3 WO 2015050592 A3 WO2015050592 A3 WO 2015050592A3 US 2014042130 W US2014042130 W US 2014042130W WO 2015050592 A3 WO2015050592 A3 WO 2015050592A3
Authority
WO
WIPO (PCT)
Prior art keywords
liner panel
gas turbine
turbine engine
combustor liner
engine combustor
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.)
Ceased
Application number
PCT/US2014/042130
Other languages
French (fr)
Other versions
WO2015050592A2 (en
Inventor
Christopher Drake
Frank J. Cunha
Stanislav KOSTKA
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.)
RTX 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 EP14850876.5A priority Critical patent/EP3008388A4/en
Priority to US14/897,725 priority patent/US20160123592A1/en
Publication of WO2015050592A2 publication Critical patent/WO2015050592A2/en
Publication of WO2015050592A3 publication Critical patent/WO2015050592A3/en
Anticipated expiration legal-status Critical
Ceased 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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R2900/03041—Effusion 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
    • 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
    • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A liner panel is provided for a combustor of a gas turbine engine. The liner panel includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a depression, where the depression includes an entrance to at least one passage through the liner panel.
PCT/US2014/042130 2013-06-14 2014-06-12 Gas turbine engine combustor liner panel Ceased WO2015050592A2 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14850876.5A EP3008388A4 (en) 2013-06-14 2014-06-12 Gas turbine engine combustor liner panel
US14/897,725 US20160123592A1 (en) 2013-06-14 2014-06-12 Gas turbine engine combustor liner panel

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US201361835153P 2013-06-14 2013-06-14
US61/835,153 2013-06-14
US201361865912P 2013-08-14 2013-08-14
US61/865,912 2013-08-14

Publications (2)

Publication Number Publication Date
WO2015050592A2 WO2015050592A2 (en) 2015-04-09
WO2015050592A3 true WO2015050592A3 (en) 2015-06-11

Family

ID=52779256

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2014/042130 Ceased WO2015050592A2 (en) 2013-06-14 2014-06-12 Gas turbine engine combustor liner panel

Country Status (3)

Country Link
US (1) US20160123592A1 (en)
EP (1) EP3008388A4 (en)
WO (1) WO2015050592A2 (en)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9624911B1 (en) 2012-10-26 2017-04-18 Sunfolding, Llc Fluidic solar actuator
DE102013214487A1 (en) * 2013-07-24 2015-01-29 Rolls-Royce Deutschland Ltd & Co Kg Combustor shingle of a gas turbine
US10753608B2 (en) 2013-11-21 2020-08-25 Raytheon Technologies Corporation Turbine engine multi-walled structure with internal cooling element(s)
MX393821B (en) 2015-01-30 2025-03-24 Sunfolding Inc FLUIDIC ACTUATOR METHOD AND SYSTEM.
US10605170B2 (en) * 2015-11-24 2020-03-31 General Electric Company Engine component with film cooling
US20170159487A1 (en) * 2015-12-02 2017-06-08 General Electric Company HT Enhancement Bumps/Features on Cold Side
DE102015225505A1 (en) * 2015-12-16 2017-06-22 Rolls-Royce Deutschland Ltd & Co Kg Wall of a component to be cooled by means of cooling air, in particular a gas turbine combustion chamber wall
EP3276128A1 (en) * 2016-07-25 2018-01-31 Siemens Aktiengesellschaft Coolable wall element
US10520197B2 (en) 2017-06-01 2019-12-31 General Electric Company Single cavity trapped vortex combustor with CMC inner and outer liners
US10731562B2 (en) 2017-07-17 2020-08-04 Raytheon Technologies Corporation Combustor panel standoffs with cooling holes
US10823414B2 (en) * 2018-03-19 2020-11-03 Raytheon Technologies Corporation Hooded entrance to effusion holes
WO2019231927A1 (en) 2018-05-29 2019-12-05 Sunfolding, Inc. Tubular fluidic actuator system and method
US10775044B2 (en) * 2018-10-26 2020-09-15 Honeywell International Inc. Gas turbine engine dual-wall hot section structure
US11209162B2 (en) * 2019-01-04 2021-12-28 Raytheon Technologies Corporation Combustor panel stud cooling effusion through heat transfer augmentors
US11112114B2 (en) 2019-07-23 2021-09-07 Raytheon Technologies Corporation Combustor panels for gas turbine engines
GB202000870D0 (en) * 2020-01-21 2020-03-04 Rolls Royce Plc A combustion chamber, a combustion chamber tile and a combustion chamber segment
TW202204834A (en) 2020-06-22 2022-02-01 美商尚府鼎公司 Locking, dampening and actuation systems and methods for solar trackers
US11965653B2 (en) 2021-06-23 2024-04-23 General Electric Company Dilution air inlets with notched tip and slotted tail for combustor
JP7614980B2 (en) * 2021-08-25 2025-01-16 三菱重工航空エンジン株式会社 Combustor panel and gas turbine combustor

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5265409A (en) * 1992-12-18 1993-11-30 United Technologies Corporation Uniform cooling film replenishment thermal liner assembly
US20050262846A1 (en) * 2001-03-12 2005-12-01 Anthony Pidcock Combustion apparatus
US20120125576A1 (en) * 2010-11-24 2012-05-24 Honeywell International Inc. Entrainment heat sink devices
EP2518429A1 (en) * 2011-04-28 2012-10-31 Siemens Aktiengesellschaft An enhanced cooling surface
JP2012211749A (en) * 2011-03-31 2012-11-01 Ihi Corp Combustor for gas turbine engine and gas turbine engine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3584972A (en) * 1966-02-09 1971-06-15 Gen Motors Corp Laminated porous metal
US4184326A (en) * 1975-12-05 1980-01-22 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
US4773593A (en) * 1987-05-04 1988-09-27 United Technologies Corporation Coolable thin metal sheet
US5758504A (en) * 1996-08-05 1998-06-02 Solar Turbines Incorporated Impingement/effusion cooled combustor liner
US6701714B2 (en) * 2001-12-05 2004-03-09 United Technologies Corporation Gas turbine combustor
US7270175B2 (en) * 2004-01-09 2007-09-18 United Technologies Corporation Extended impingement cooling device and method
US7820267B2 (en) * 2007-08-20 2010-10-26 Honeywell International Inc. Percussion drilled shaped through hole and method of forming
US20120000072A9 (en) * 2008-09-26 2012-01-05 Morrison Jay A Method of Making a Combustion Turbine Component Having a Plurality of Surface Cooling Features and Associated Components
DE102013003444A1 (en) * 2013-02-26 2014-09-11 Rolls-Royce Deutschland Ltd & Co Kg Impact-cooled shingle of a gas turbine combustor with extended effusion holes
US9010125B2 (en) * 2013-08-01 2015-04-21 Siemens Energy, Inc. Regeneratively cooled transition duct with transversely buffered impingement nozzles

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5265409A (en) * 1992-12-18 1993-11-30 United Technologies Corporation Uniform cooling film replenishment thermal liner assembly
US20050262846A1 (en) * 2001-03-12 2005-12-01 Anthony Pidcock Combustion apparatus
US20120125576A1 (en) * 2010-11-24 2012-05-24 Honeywell International Inc. Entrainment heat sink devices
JP2012211749A (en) * 2011-03-31 2012-11-01 Ihi Corp Combustor for gas turbine engine and gas turbine engine
EP2518429A1 (en) * 2011-04-28 2012-10-31 Siemens Aktiengesellschaft An enhanced cooling surface

Also Published As

Publication number Publication date
WO2015050592A2 (en) 2015-04-09
US20160123592A1 (en) 2016-05-05
EP3008388A4 (en) 2016-07-20
EP3008388A2 (en) 2016-04-20

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