WO2018219611A1 - Aube de stator de compresseur pour compresseurs axiaux ayant un contour ondulé de pointe - Google Patents

Aube de stator de compresseur pour compresseurs axiaux ayant un contour ondulé de pointe Download PDF

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Publication number
WO2018219611A1
WO2018219611A1 PCT/EP2018/061959 EP2018061959W WO2018219611A1 WO 2018219611 A1 WO2018219611 A1 WO 2018219611A1 EP 2018061959 W EP2018061959 W EP 2018061959W WO 2018219611 A1 WO2018219611 A1 WO 2018219611A1
Authority
WO
WIPO (PCT)
Prior art keywords
chord
airfoil
wave crest
compressor
wave
Prior art date
Application number
PCT/EP2018/061959
Other languages
English (en)
Inventor
Christian Cornelius
Stephan Klumpp
David Monk
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2018219611A1 publication Critical patent/WO2018219611A1/fr

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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/125—Fluid guiding means, e.g. vanes related to the tip 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated

Abstract

En résumé, l'invention concerne une aube de stator de compresseur (14) qui est destinée à des compresseurs axiaux (10) et qui comprend un profilé (22) en porte-à-faux fixé à un carter de compresseur (18) par l'intermédiaire d'un pied de pale, le profilé (22) comportant une pointe (28) de profilé, s'étendant d'un bord d'attaque (34) à un bord de fuite (35). Pour améliorer l'efficacité aérodynamique, il est proposé une pointe (28) de profilé ondulée, qui expose une forme de type ondulation ayant au moins une crête d'ondulation (38). Pour réduire encore davantage les écoulements parasites de fuite secondaires, la pointe (28) de profilé comprend un premier creux (42) et une seconde crête d'ondulation (40). L'amplitude de la première crête (38) est supérieure à l'amplitude de la seconde crête (40). En outre, la paroi d'extrémité de moyeu de rotor en vis-à-vis (30) peut être formée en conséquence. Ainsi, la longueur et la position de tourbillonnement de fuite de pointe sont décalées sensiblement en amont, réduisant ainsi les pertes globales de pointe et réduisant le blocage du passage d'écoulement, ce qui améliore doublement l'efficacité du compresseur.
PCT/EP2018/061959 2017-06-01 2018-05-09 Aube de stator de compresseur pour compresseurs axiaux ayant un contour ondulé de pointe WO2018219611A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201762513494P 2017-06-01 2017-06-01
US62/513,494 2017-06-01

Publications (1)

Publication Number Publication Date
WO2018219611A1 true WO2018219611A1 (fr) 2018-12-06

Family

ID=62245230

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2018/061959 WO2018219611A1 (fr) 2017-06-01 2018-05-09 Aube de stator de compresseur pour compresseurs axiaux ayant un contour ondulé de pointe

Country Status (1)

Country Link
WO (1) WO2018219611A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3690189A1 (fr) * 2019-01-31 2020-08-05 United Technologies Corporation Paroi d'extrémité profilée pour un moteur à turbine à gaz
CN114109522A (zh) * 2021-11-29 2022-03-01 清华大学 控制间隙损失的导叶结构和动力系统
CN114251130A (zh) * 2021-12-22 2022-03-29 清华大学 一种用于控制叶顶泄漏流的鲁棒性转子结构和动力系统
CN114517794A (zh) * 2022-03-01 2022-05-20 大连海事大学 一种跨音速轴流压气机联合机匣处理结构
CN114962329A (zh) * 2022-05-27 2022-08-30 哈尔滨工程大学 一种新型的压气机转子间隙结构及应用

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1531233A2 (fr) * 2003-11-12 2005-05-18 MTU Aero Engines GmbH Turbine à gaz conprenant des aubes statoriques ayant différentes courbures radiales
EP1840332A1 (fr) * 2006-03-27 2007-10-03 Siemens Aktiengesellschaft Aube de turbomachine et turbomachine
DE102010050185A1 (de) * 2010-10-30 2012-05-03 Deutsches Zentrum für Luft- und Raumfahrt e.V. Axialturbomaschine
US20150369071A1 (en) * 2013-02-05 2015-12-24 United Technologies Corporation Gas turbine engine component having tip vortex creation feature

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1531233A2 (fr) * 2003-11-12 2005-05-18 MTU Aero Engines GmbH Turbine à gaz conprenant des aubes statoriques ayant différentes courbures radiales
EP1840332A1 (fr) * 2006-03-27 2007-10-03 Siemens Aktiengesellschaft Aube de turbomachine et turbomachine
DE102010050185A1 (de) * 2010-10-30 2012-05-03 Deutsches Zentrum für Luft- und Raumfahrt e.V. Axialturbomaschine
US20150369071A1 (en) * 2013-02-05 2015-12-24 United Technologies Corporation Gas turbine engine component having tip vortex creation feature

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
CHRISTOF LECHNER; JORG SEUME: "Stationare Gasturbinen", 2003, SPRINER-VERLAG BELIN, pages: 310

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3690189A1 (fr) * 2019-01-31 2020-08-05 United Technologies Corporation Paroi d'extrémité profilée pour un moteur à turbine à gaz
US10920599B2 (en) 2019-01-31 2021-02-16 Raytheon Technologies Corporation Contoured endwall for a gas turbine engine
CN114109522A (zh) * 2021-11-29 2022-03-01 清华大学 控制间隙损失的导叶结构和动力系统
CN114109522B (zh) * 2021-11-29 2022-12-02 清华大学 控制间隙损失的导叶结构和动力系统
CN114251130A (zh) * 2021-12-22 2022-03-29 清华大学 一种用于控制叶顶泄漏流的鲁棒性转子结构和动力系统
CN114251130B (zh) * 2021-12-22 2022-12-02 清华大学 一种用于控制叶顶泄漏流的鲁棒性转子结构和动力系统
CN114517794A (zh) * 2022-03-01 2022-05-20 大连海事大学 一种跨音速轴流压气机联合机匣处理结构
CN114962329A (zh) * 2022-05-27 2022-08-30 哈尔滨工程大学 一种新型的压气机转子间隙结构及应用
CN114962329B (zh) * 2022-05-27 2024-04-26 哈尔滨工程大学 一种压气机转子间隙结构及应用

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