[go: up one dir, main page]
More Web Proxy on the site http://driver.im/

MX359150B - Un componente de turbomáquina con una cavidad de alivio de tensión. - Google Patents

Un componente de turbomáquina con una cavidad de alivio de tensión.

Info

Publication number
MX359150B
MX359150B MX2015009316A MX2015009316A MX359150B MX 359150 B MX359150 B MX 359150B MX 2015009316 A MX2015009316 A MX 2015009316A MX 2015009316 A MX2015009316 A MX 2015009316A MX 359150 B MX359150 B MX 359150B
Authority
MX
Mexico
Prior art keywords
stress relief
relief cavity
turbomachine component
trailing edge
platform
Prior art date
Application number
MX2015009316A
Other languages
English (en)
Other versions
MX2015009316A (es
Inventor
Häggmark Anders
Szijarto Janos
Original Assignee
Siemens Ag
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 Siemens Ag filed Critical Siemens Ag
Publication of MX2015009316A publication Critical patent/MX2015009316A/es
Publication of MX359150B publication Critical patent/MX359150B/es

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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
    • B23H9/10—Working turbine blades or nozzles
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Se proporciona un componente de turbomáquina (1) con una cavidad de alivio de tensión (30). El componente de turbomáquina contiene una superficie aerodinámica (10) y una plataforma (20). La superficie aerodinámica contiene un borde posterior (28). La plataforma contiene una zona de borde posterior (25), una ranura de banda de sellado (40) y una cavidad de alivio de tensión (30). La zona de borde posterior (25) soporta al menos una parte del borde posterior (28). La cavidad de alivio de tensión (30) se extiende dentro de la plataforma en la zona de borde posterior (25) y es una extensión de la ranura de banda de sellado (40).
MX2015009316A 2013-03-20 2014-02-10 Un componente de turbomáquina con una cavidad de alivio de tensión. MX359150B (es)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP13160209.6A EP2781697A1 (en) 2013-03-20 2013-03-20 A turbomachine component with a stress relief cavity and method of forming such a cavity
PCT/EP2014/052547 WO2014146827A1 (en) 2013-03-20 2014-02-10 A turbomachine component with a stress relief cavity

Publications (2)

Publication Number Publication Date
MX2015009316A MX2015009316A (es) 2015-09-29
MX359150B true MX359150B (es) 2018-09-17

Family

ID=47913158

Family Applications (1)

Application Number Title Priority Date Filing Date
MX2015009316A MX359150B (es) 2013-03-20 2014-02-10 Un componente de turbomáquina con una cavidad de alivio de tensión.

Country Status (7)

Country Link
US (1) US10001017B2 (es)
EP (2) EP2781697A1 (es)
CN (1) CN105283639B (es)
IN (1) IN2015DN04077A (es)
MX (1) MX359150B (es)
RU (1) RU2666715C2 (es)
WO (1) WO2014146827A1 (es)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10030530B2 (en) * 2014-07-31 2018-07-24 United Technologies Corporation Reversible blade rotor seal
US10036263B2 (en) * 2014-10-22 2018-07-31 United Technologies Corporation Stator assembly with pad interface for a gas turbine engine
US10941671B2 (en) 2017-03-23 2021-03-09 General Electric Company Gas turbine engine component incorporating a seal slot
CN107143381A (zh) * 2017-06-06 2017-09-08 哈尔滨汽轮机厂有限责任公司 一种能够降低应力的燃气轮机透平第一级动叶片
US10323520B2 (en) * 2017-06-13 2019-06-18 General Electric Company Platform cooling arrangement in a turbine rotor blade
EP3438410B1 (en) 2017-08-01 2021-09-29 General Electric Company Sealing system for a rotary machine
US10907491B2 (en) * 2017-11-30 2021-02-02 General Electric Company Sealing system for a rotary machine and method of assembling same
US11111802B2 (en) * 2019-05-01 2021-09-07 Raytheon Technologies Corporation Seal for a gas turbine engine

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6210111B1 (en) * 1998-12-21 2001-04-03 United Technologies Corporation Turbine blade with platform cooling
US6761536B1 (en) * 2003-01-31 2004-07-13 Power Systems Mfg, Llc Turbine blade platform trailing edge undercut
US6951447B2 (en) 2003-12-17 2005-10-04 United Technologies Corporation Turbine blade with trailing edge platform undercut
US7731482B2 (en) * 2006-06-13 2010-06-08 General Electric Company Bucket vibration damper system
US7922444B2 (en) * 2007-01-19 2011-04-12 United Technologies Corporation Chamfer rail pockets for turbine vane shrouds
US8282354B2 (en) * 2008-04-16 2012-10-09 United Technologies Corporation Reduced weight blade for a gas turbine engine
CH699998A1 (de) * 2008-11-26 2010-05-31 Alstom Technology Ltd Leitschaufel für eine Gasturbine.
US8096757B2 (en) 2009-01-02 2012-01-17 General Electric Company Methods and apparatus for reducing nozzle stress
US8684664B2 (en) * 2010-09-30 2014-04-01 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US8584512B2 (en) * 2010-12-13 2013-11-19 Pcc Airfoils, Inc. Method and apparatus for inspecting airfoils
US8550783B2 (en) * 2011-04-01 2013-10-08 Alstom Technology Ltd. Turbine blade platform undercut

Also Published As

Publication number Publication date
RU2015144864A (ru) 2017-04-26
IN2015DN04077A (es) 2015-10-09
WO2014146827A1 (en) 2014-09-25
US10001017B2 (en) 2018-06-19
EP2917501A1 (en) 2015-09-16
RU2666715C2 (ru) 2018-09-11
MX2015009316A (es) 2015-09-29
EP2781697A1 (en) 2014-09-24
CN105283639B (zh) 2019-04-30
US20160017716A1 (en) 2016-01-21
CN105283639A (zh) 2016-01-27

Similar Documents

Publication Publication Date Title
MX2015009316A (es) Un componente de turbomaquinacion una cavidad de alivio de tension.
EP2799721B8 (fr) Redresseur de turbomachine axiale avec aubes auxiliaires en pieds d'aubes
MX2017008368A (es) Pala con perfil alar y metodo de armado.
WO2013165527A3 (en) High order shaped curve region for an airfoil
WO2014175937A3 (en) Gas turbine engine component having curved turbulator
WO2013154657A3 (en) Turbine blade damper seal
BR112015028251A2 (pt) aerofólio compósito
EP3027853A4 (en) Gas turbine engine cmc airfoil assembly
EP3044427B8 (en) Gas turbine engine and corresponding method for regulating blade tip clearance
WO2015057310A3 (en) Platform cooling core for a gas turbine engine rotor blade
EP2977556B8 (en) Airfoil, gas turbine engine assembly, and corresponding cooling method
EP3074606A4 (en) Gas turbine engine airfoil with leading edge trench and impingement cooling
BR112015001828A2 (pt) tira protetora, aerofólio de uma turbomáquina, método de fabricação de um aerofólio e aerofólio com a tira protetora
WO2013130181A3 (en) Low loss airfoil platform trailing edge
EP3063374A4 (en) Gas turbine engine airfoil with auxiliary flow channel
EP3090131B8 (en) Airfoil, corresponding gas turbine engine and method for reducing airfoil tip leakage losses
EP3004558A4 (en) SIDE COOLING SURFACE SURFACE LEAK EDGE SUCTION FOR GAS TURBINE
WO2014171994A3 (en) Borescope plug assembly for gas turbine engine
GB2527001A (en) A transition arrangement for an aircraft
WO2014186005A3 (en) Gas turbine engine component with combined mate face and platform cooling
WO2014204542A3 (en) Lightweight blade for gas turbine engine
EP3670839A4 (en) GAS TURBINE STATOR VANE AND GAS TURBINE EQUIPPED WITH THE LATEST
MX2016009913A (es) Aspa de ventilador con borde delantero escalonado.
EP2952685B8 (en) Airfoil for a gas turbine engine, a gas turbine engine and a method for reducing frictional heating between airfoils and a case of a gas turbine engine
GB2519845B (en) Blisk with low stresses at blade root, preferably for an aircraft turbine engine fan

Legal Events

Date Code Title Description
FG Grant or registration