ES2570969T3 - Grado de turbina de gas - Google Patents

Grado de turbina de gas

Info

Publication number
ES2570969T3
ES2570969T3 ES13176420T ES13176420T ES2570969T3 ES 2570969 T3 ES2570969 T3 ES 2570969T3 ES 13176420 T ES13176420 T ES 13176420T ES 13176420 T ES13176420 T ES 13176420T ES 2570969 T3 ES2570969 T3 ES 2570969T3
Authority
ES
Spain
Prior art keywords
blade
arrangement
impeller blades
director
front surface
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.)
Active
Application number
ES13176420T
Other languages
English (en)
Inventor
Mahle Inga Dr
Norbert Hübner
Rudolf Stanka
Gottfried Schütz
Norman Cleesattel
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Application granted granted Critical
Publication of ES2570969T3 publication Critical patent/ES2570969T3/es
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • 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
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Grado de turbina de gas con una disposición de álabes de rodete con varios álabes de rodete (1) y una disposición de álabes directores contigua con varios álabes directores (2) con bordes delanteros de la hoja del álabe director (2.1), que están opuestos a la disposición de álabes de rodete, que se caracteriza por que una ranura axial (A) mínima está conformada entre la disposición de álabes de rodete y la disposición de álabes directores, en una primera posición radial de una superficie frontal (1.2) de la disposición de álabes de rodete, entre esta superficie frontal y una primera zona de contacto (Ka) opuesta a la misma, de al menos, uno de los bordes delanteros de hoja de álabe director, y en una segunda posición radial distinta a ésta de la superficie frontal, la ranura axial (A) mínima está conformada entre la superficie frontal y una segunda zona de contacto (K¡), opuesta a la misma, de este borde delantero de la hoja de álabe director, presentando este borde delantero de la hoja de álabe director, entre la primera y la segunda zona de contacto, un desplazamiento axial de máximo 0,6% de una altura radial del borde delantero de la hoja de álabe director.
ES13176420T 2013-07-12 2013-07-12 Grado de turbina de gas Active ES2570969T3 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13176420.1A EP2824277B1 (de) 2013-07-12 2013-07-12 Gasturbinenstufe

Publications (1)

Publication Number Publication Date
ES2570969T3 true ES2570969T3 (es) 2016-05-23

Family

ID=48795429

Family Applications (1)

Application Number Title Priority Date Filing Date
ES13176420T Active ES2570969T3 (es) 2013-07-12 2013-07-12 Grado de turbina de gas

Country Status (3)

Country Link
US (1) US9617863B2 (es)
EP (1) EP2824277B1 (es)
ES (1) ES2570969T3 (es)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2932601C (en) 2015-06-17 2023-10-03 Rolls-Royce Corporation Labyrinth seal with tunable flow splitter
US10815824B2 (en) 2017-04-04 2020-10-27 General Electric Method and system for rotor overspeed protection
US11408300B2 (en) 2018-12-03 2022-08-09 Raytheon Technologies Corporation Rotor overspeed protection assembly
CN114837752B (zh) * 2021-02-02 2024-11-26 中国航发商用航空发动机有限责任公司 航空发动机
CN114961880B (zh) * 2021-02-22 2024-07-23 中国航发商用航空发动机有限责任公司 航空发动机

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1008526A (en) * 1964-04-09 1965-10-27 Rolls Royce Axial flow bladed rotor, e.g. for a turbine
US4238170A (en) * 1978-06-26 1980-12-09 United Technologies Corporation Blade tip seal for an axial flow rotary machine
US4645417A (en) * 1984-02-06 1987-02-24 General Electric Company Compressor casing recess
DE4344189C1 (de) * 1993-12-23 1995-08-03 Mtu Muenchen Gmbh Axial-Schaufelgitter mit gepfeilten Schaufelvorderkanten
US5645399A (en) * 1995-03-15 1997-07-08 United Technologies Corporation Gas turbine engine case coated with thermal barrier coating to control axial airfoil clearance
US6120242A (en) * 1998-11-13 2000-09-19 General Electric Company Blade containing turbine shroud
US6312219B1 (en) 1999-11-05 2001-11-06 General Electric Company Narrow waist vane
FR2875842B1 (fr) * 2004-09-28 2010-09-24 Snecma Moteurs Dispositif de limitation de survitesse de turbine dans une turbomachine
EP2140111B1 (de) * 2007-04-24 2014-05-07 Alstom Technology Ltd Strömungsmaschine
US8439626B2 (en) * 2008-12-29 2013-05-14 General Electric Company Turbine airfoil clocking
US8562289B2 (en) * 2010-02-26 2013-10-22 Ge Aviation Systems, Llc Method and system for a leakage controlled fan housing
US8734113B2 (en) * 2010-07-26 2014-05-27 Snecma Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the fourth stage of a turbine
US9037434B2 (en) * 2012-01-03 2015-05-19 General Electric Company Method and apparatus for obtaining discrete axial clearance data using radial clearance sensors

Also Published As

Publication number Publication date
US9617863B2 (en) 2017-04-11
EP2824277A1 (de) 2015-01-14
US20150016985A1 (en) 2015-01-15
EP2824277B1 (de) 2016-03-23

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