WO2014039826A8 - Gas turbine engine compressor undercut spacer - Google Patents

Gas turbine engine compressor undercut spacer Download PDF

Info

Publication number
WO2014039826A8
WO2014039826A8 PCT/US2013/058515 US2013058515W WO2014039826A8 WO 2014039826 A8 WO2014039826 A8 WO 2014039826A8 US 2013058515 W US2013058515 W US 2013058515W WO 2014039826 A8 WO2014039826 A8 WO 2014039826A8
Authority
WO
WIPO (PCT)
Prior art keywords
gas turbine
turbine engine
engine compressor
lip
undercut
Prior art date
Application number
PCT/US2013/058515
Other languages
French (fr)
Other versions
WO2014039826A1 (en
Inventor
Engward William Nielsen
Kenneth Blair HURST
II Victor Manuel SIORDIA
Original Assignee
Solar Turbines Incorporated
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 Solar Turbines Incorporated filed Critical Solar Turbines Incorporated
Priority to GB201501901A priority Critical patent/GB2520203A/en
Priority to CN201380045772.0A priority patent/CN104822919B/en
Publication of WO2014039826A1 publication Critical patent/WO2014039826A1/en
Publication of WO2014039826A8 publication Critical patent/WO2014039826A8/en

Links

Classifications

    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections

Abstract

A gas turbine engine compressor spacer (230) includes a body (229) with a hollow cylinder shape. The body (229) includes an outer surface (232) with an axially forward end. The body (229) also includes a forward face (233) extending radially inward from the axially forward end. A forward lip (237) extends axially from the body (229). The forward lip (237) includes a forward lip surface (239) located radially inward from the forward face (233). The forward lip surface (239) is the radially outer circumferential surface of the forward lip (237). The spacer (230) also includes a forward undercut (235). The forward undercut (235) is located between the forward face (233) and the forward lip surface (239).
PCT/US2013/058515 2012-09-06 2013-09-06 Gas turbine engine compressor undercut spacer WO2014039826A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB201501901A GB2520203A (en) 2012-09-06 2013-09-06 Gas turbine engine compressor undercut spacer
CN201380045772.0A CN104822919B (en) 2012-09-06 2013-09-06 Gas-turbine compressor undercuts distance piece

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/605,615 2012-09-06
US13/605,615 US20140064946A1 (en) 2012-09-06 2012-09-06 Gas turbine engine compressor undercut spacer

Publications (2)

Publication Number Publication Date
WO2014039826A1 WO2014039826A1 (en) 2014-03-13
WO2014039826A8 true WO2014039826A8 (en) 2015-06-11

Family

ID=50187858

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2013/058515 WO2014039826A1 (en) 2012-09-06 2013-09-06 Gas turbine engine compressor undercut spacer

Country Status (3)

Country Link
US (1) US20140064946A1 (en)
CN (1) CN104822919B (en)
WO (1) WO2014039826A1 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2015106548A (en) * 2013-12-03 2015-06-08 矢崎総業株式会社 Method of crimping wire to terminal
US9724785B2 (en) * 2014-05-15 2017-08-08 Solar Turbines Incorporated Radiographic markers for partial penetration welded joints
US10385695B2 (en) * 2014-08-14 2019-08-20 Pratt & Whitney Canada Corp. Rotor for gas turbine engine
US10125785B2 (en) * 2015-10-16 2018-11-13 Pratt & Whitney Reduced stress rotor interface
US10738639B2 (en) 2016-05-17 2020-08-11 Raytheon Technologies Corporation Curvic seal fitting and balance weight locations
US10584599B2 (en) 2017-07-14 2020-03-10 United Technologies Corporation Compressor rotor stack assembly for gas turbine engine
US10669875B2 (en) * 2018-03-28 2020-06-02 Solar Turbines Incorporated Cross key anti-rotation spacer
FR3092779B1 (en) * 2019-02-19 2021-02-26 Safran Aircraft Engines Improved tooling for coating wipers
DE102021126427A1 (en) 2021-10-12 2023-04-13 MTU Aero Engines AG Rotor arrangement for a gas turbine with inclined axial contact surfaces formed on rotor segments, gas turbine and aircraft gas turbine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479046A (en) * 1944-08-23 1949-08-16 United Aircraft Corp Limiting heat transfer to the turbine rotor
JP3621523B2 (en) * 1996-09-25 2005-02-16 株式会社東芝 Gas turbine rotor blade cooling system
JP2005220825A (en) * 2004-02-06 2005-08-18 Mitsubishi Heavy Ind Ltd Turbine moving blade
US7059831B2 (en) * 2004-04-15 2006-06-13 United Technologies Corporation Turbine engine disk spacers
JP4412081B2 (en) * 2004-07-07 2010-02-10 株式会社日立製作所 Gas turbine and gas turbine cooling method
EP1970533A1 (en) * 2007-03-12 2008-09-17 Siemens Aktiengesellschaft Turbine with at least one rotor with rotor disks and a tie bolt
EP2045444B1 (en) * 2007-10-01 2015-11-18 Alstom Technology Ltd Rotor blade, method for producing a rotor blade, and compressor with such a rotor blade
US8727695B2 (en) * 2009-12-09 2014-05-20 Rolls-Royce Corporation Chamfer-fillet gap for thermal management
US8459943B2 (en) * 2010-03-10 2013-06-11 United Technologies Corporation Gas turbine engine rotor sections held together by tie shaft, and with blade rim undercut
US20120099995A1 (en) * 2010-10-20 2012-04-26 General Electric Company Rotary machine having spacers for control of fluid dynamics

Also Published As

Publication number Publication date
CN104822919B (en) 2017-03-15
US20140064946A1 (en) 2014-03-06
WO2014039826A1 (en) 2014-03-13
CN104822919A (en) 2015-08-05

Similar Documents

Publication Publication Date Title
WO2014039826A8 (en) Gas turbine engine compressor undercut spacer
WO2015002673A3 (en) Gas turbine engine seal assembly
WO2014028090A3 (en) Blade outer air seal for a gas turbine engine
WO2014175937A3 (en) Gas turbine engine component having curved turbulator
WO2014175969A3 (en) Engine mid-turbine frame transfer tube for low pressure turbine case cooling
WO2014007886A3 (en) Turbomachine thermal management
EP2256383A3 (en) Face seal for gas turbine engine
EP2518274A3 (en) Blade clearance control using high-CTE and low-CTE ring members
EP2977618A3 (en) Gas turbine engine with a blade track assembly and corresponding assembly method
EP2610471A3 (en) Seal for a variable area fan nozzle
EP2650487A3 (en) Turbine shroud assembly, corresponding turbine assembly and method of forming
WO2015023345A3 (en) Composite airfoil metal patch
WO2015147929A3 (en) Cooling an aperture body of a combustor wall
WO2014133647A3 (en) Circumferentially retained fairing
WO2015069338A3 (en) Gas turbine engine blade outer air seal thermal control system
WO2015112225A3 (en) Gas turbine engine airfoil with leading edge trench and impingement cooling
EP2662532A3 (en) Turbine assembly with expansion seal
EP2586992A3 (en) Rotating vane seal with cooling air passages
EP2546463A3 (en) Blade outer air seal having partial coating
EP2615259A3 (en) Gas turbine engine bearing chamber seals
WO2014197024A3 (en) Full ring curvic seal
WO2012166601A3 (en) Cylinder liner with a case on a cuff-ring groove
WO2014133649A3 (en) Component retention with probe
WO2014186000A3 (en) Twisted gas turbine engine airfoil having a twisted rib
WO2015017002A3 (en) Swirler mount interface for gas turbine engine combustor

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 13834683

Country of ref document: EP

Kind code of ref document: A1

ENP Entry into the national phase

Ref document number: 1501901

Country of ref document: GB

Kind code of ref document: A

Free format text: PCT FILING DATE = 20130906

WWE Wipo information: entry into national phase

Ref document number: 1501901.1

Country of ref document: GB

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 13834683

Country of ref document: EP

Kind code of ref document: A1