EP1959096B1 - Procédé de refroidissement d'un élément d'une turbomachine par jet - Google Patents

Procédé de refroidissement d'un élément d'une turbomachine par jet Download PDF

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Publication number
EP1959096B1
EP1959096B1 EP08151497.8A EP08151497A EP1959096B1 EP 1959096 B1 EP1959096 B1 EP 1959096B1 EP 08151497 A EP08151497 A EP 08151497A EP 1959096 B1 EP1959096 B1 EP 1959096B1
Authority
EP
European Patent Office
Prior art keywords
cooling
air
impingement
cooling air
cool
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
EP08151497.8A
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German (de)
English (en)
Other versions
EP1959096A3 (fr
EP1959096A2 (fr
Inventor
Janetzke Dr. Timm
Dr. Woflgang Nitsche Prof.
Reyer Dr. Matthias
Haselbach Dr. Frank
Janke Dr. Erik
Täge Jens
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1959096A2 publication Critical patent/EP1959096A2/fr
Publication of EP1959096A3 publication Critical patent/EP1959096A3/fr
Application granted granted Critical
Publication of EP1959096B1 publication Critical patent/EP1959096B1/fr
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D5/187—Convection cooling
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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

Definitions

  • the invention relates to a method for impingement air cooling for gas turbines, in which cooling air impinges on formed in a partition impingement air openings in separate cooling air jets on the wall to be cooled wall area.
  • impingement air cooling In gas turbine engines and stationary gas turbines, it is known to cool the highly heated components in the turbine such as rotor blades, vanes, liners or combustion chamber walls with a portion of the compressor air by means of impingement air.
  • impingement air cooling the cooling air, as a steady stream of air, reaches the surface to be cooled via relatively small impingement cooling bores. Due to the strong pressure drop in the impingement cooling bores in each case a powerful air jet is formed, which causes a high heat transfer in each case in a localized area of the wall surface to be cooled.
  • the EP 0 892 151 A1 For example, a channel formed in the leading edge of a turbine blade is exposed to impingement air via cooling holes from a main channel supplied with cooling air and is passed longitudinally through the blade height. An optimal cooling effect of the impact air jets is not achieved in this way.
  • the disclosed EP 0 698 724 B1 a special blade formation for impingement air cooling of the trailing edge of a turbine blade with which the cooling effect of the impingement air reduced by crossflows in the impingement cooling air streams is to be improved.
  • the EP 0 889 201 A1 suggests a specific shape of the wall surface to be cooled in order to increase the cooling effect of the impingement air jets.
  • the invention has for its object to provide a method for the impact air cooling acted upon by hot combustion gases components of a gas turbine, with which the cooling effect of the impact air can be improved. According to the invention the object is achieved by a method according to the features of patent claim 1. From the dependent claims, further features and advantageous developments of the invention.
  • the basic idea of the invention is that ring vortex structures are produced in the space between the impingement air openings and the wall of the engine component to be cooled instead of a continuous impingement air stream at a distance by the impingement air openings on the input side with in a certain frequency and with certain amplitude with cooling air pulses be charged.
  • At a certain amplitude of the cooling air pulses and a matched size of the impingement air openings are strong Ringwirbelstruk-tures
  • the temperature gradients on the component wall become due to the dynamic response behavior of the temperature boundary layer on average over time higher and thereby the heat transfer is increased on the wall of the component to be cooled.
  • Ring vortex structures for maximum cooling effect highest intensity are achieved by a correspondingly larger amplitude, preferably at a certain resonant frequency
  • the distance between the partition wall and the wall region to be cooled is chosen according to the invention such that resonance conditions prevail between the ring vortices generated at the impact air openings and the pressure waves induced and reflected due to the occurring ring vortices and thus an intensification of the ring vortex structures can be observed.
  • the periodic generation of the ring vortex structures is interrupted at regular intervals, by the regularly recurring pauses in the periodic ring vorticity of the cooling air mass flow can be reduced with the same cooling effect.
  • the improved cooling effect due to the ring vortex structures of the impingement air generated in a certain frequency reduces the cooling air requirement and increases the efficiency of the turbine or the life of the highly heated turbine components.
  • a cavity 1 of an engine component for example, a blade of a turbine stage
  • a temperature T cool a time-varying, ie in the speed periodically - for example, sinusoidal - changing cooling air mass flow, consisting of at a time interval consecutive cooling air velocity sacred V cool (t) with a certain amplitude V cool , introduced.
  • a hot gas with a temperature T and a velocity V flows along the outer wall 3 of the engine component to be cooled.
  • a partition wall 2 with impact air openings 4 is arranged at a distance from the outer wall 3, which with the temporally successive speed packets V cool (t ) of the unsteady cooling air mass flow are applied.
  • the cooling air reaches the inner surface of the outer wall 3 and flows in a transverse flow at the speed V cross in the cooling air channel formed between the outer wall 3 and the partition 2 5 via openings, not shown, for example, film cooling holes, to the outside. Due to the periodic loading of the impingement air openings 4 with the cooling air velocity packets V cool (t), periodically successive strong ring vortex structures 6 are formed at their exit when they impinge on the transverse flow.
  • the annular vortex structures 6 of the cooling air are able to substantially completely penetrate the cooling air channel 5 present between the dividing wall and the outer wall or the transverse flow present in the outer wall and thus strike the inner surface of the outer wall 3 with high intensity, which is better than with is cooled according to the prior art provided a steady impingement air flow.
  • the new cooling method can be used on stationary gas turbines and gas turbine engines for impingement air cooling of rotor blades, vanes, liners and platforms as well as turbine and combustor housings.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (5)

  1. Procédé de refroidissement d'air d'impact pour turbines à gaz, dans lequel de l'air de refroidissement percute en jets d'air de refroidissement séparés la zone de paroi à refroidir en passant par des orifices d'air d'impact formés dans une cloison et est de nouveau évacué dans un flux transversal, dans lequel que dans le flux transversal sont générées à intervalles de temps successifs des structures de tourbillonnement annulaire (6) à fort effet réfrigérant qui, avec une intensité et une fréquence élevées, traversent le flux transversal et percutent la zone de paroi à refroidir, par le fait que les orifices d'air d'impact (4) sont alimentés côté entrée avec des paquets de vélocité d'air de refroidissement (Vcool(t)) d'une amplitude (Vcool) et d'une fréquence (f) définies, dans lequel le rapport entre la fréquence (f) et l'amplitude (Vcool) des paquets de vélocité d'air de refroidissement et la taille (D) des orifices d'air d'impact (4) est déterminé par le nombre de Strouhal (Sr = f x D/Vcool), et qu'afin d'exciter les structures de tourbillonnement annulaire, le nombre de Strouhal (Sr) se situe dans la plage comprise entre 0,2 et 2,0.
  2. Procédé selon la revendication 1, caractérisé en ce que la formation et l'intensité des structures de tourbillonnement annulaire (6) sont déterminées par l'amplitude des paquets de vélocité d'air de refroidissement et la taille (D) des orifices d'air d'impact (4).
  3. Procédé selon la revendication 1, caractérisé en ce que le nombre d'excitation de Strouhal se situe dans la plage comprise entre 0,8 et 1,2.
  4. Procédé selon la revendication 1, caractérisé en ce que pour intensifier les structures de tourbillonnement annulaire, la distance entre la cloison et la zone de paroi à refroidir est définie de manière telle que dans l'espace entre la cloison et la paroi à refroidir règnent des conditions de résonance entre les tourbillons annulaires sur les orifices d'air d'impact et les ondes de pression réfléchies.
  5. Procédé selon la revendication 1, caractérisé en ce que la création périodique des structures de tourbillonnement annulaire (6) est interrompue à intervalles de temps réguliers afin d'économiser de l'air de refroidissement.
EP08151497.8A 2007-02-16 2008-02-15 Procédé de refroidissement d'un élément d'une turbomachine par jet Ceased EP1959096B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102007008319A DE102007008319A1 (de) 2007-02-16 2007-02-16 Verfahren zur Prallluftkühlung für Gasturbinen

Publications (3)

Publication Number Publication Date
EP1959096A2 EP1959096A2 (fr) 2008-08-20
EP1959096A3 EP1959096A3 (fr) 2013-02-20
EP1959096B1 true EP1959096B1 (fr) 2014-10-01

Family

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EP08151497.8A Ceased EP1959096B1 (fr) 2007-02-16 2008-02-15 Procédé de refroidissement d'un élément d'une turbomachine par jet

Country Status (3)

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US (1) US8152463B2 (fr)
EP (1) EP1959096B1 (fr)
DE (1) DE102007008319A1 (fr)

Families Citing this family (8)

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Publication number Priority date Publication date Assignee Title
US9458855B2 (en) 2010-12-30 2016-10-04 Rolls-Royce North American Technologies Inc. Compressor tip clearance control and gas turbine engine
DE102011078138A1 (de) 2011-06-27 2012-12-27 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung und Verfahren zur Erzeugung eines Ringwirbel ausbildenden Prallstrahls sowie Turbomaschine mit einer derartigen Vorrichtung
US9482249B2 (en) * 2013-09-09 2016-11-01 General Electric Company Three-dimensional printing process, swirling device and thermal management process
DE102013112725A1 (de) 2013-11-19 2015-05-21 Hochschule Karlsruhe Prallstrahlkühlvorrichtung
US10208603B2 (en) 2014-11-18 2019-02-19 United Technologies Corporation Staggered crossovers for airfoils
CN105927288A (zh) * 2016-06-02 2016-09-07 西北工业大学 一种转子件凸台式周期性压力波产生装置
US10480327B2 (en) 2017-01-03 2019-11-19 General Electric Company Components having channels for impingement cooling
CN113153444B (zh) * 2021-04-09 2022-12-09 西安交通大学 一种基于超声波强化传热的透平叶片内部冲击冷却结构

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DE2010607A1 (de) * 1969-03-08 1970-09-24 Rolls-Royce Ltd., Derby (Großbritannien) Flugzeugstrahltriebwerk
US4095417A (en) * 1976-08-23 1978-06-20 Avco Corporation Apparatus for and method of suppressing infrared radiation emitted from gas turbine engine
IN170251B (fr) * 1987-04-16 1992-03-07 Luminis Pty Ltd
JP3415663B2 (ja) 1992-12-28 2003-06-09 アルストム 冷却面を衝撃式に冷却するための装置
DE4244302C2 (de) * 1992-12-28 2002-08-29 Alstom Vorrichtung zur Prallkühlung
US5391052A (en) * 1993-11-16 1995-02-21 General Electric Co. Impingement cooling and cooling medium retrieval system for turbine shrouds and methods of operation
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GB2326706A (en) * 1997-06-25 1998-12-30 Europ Gas Turbines Ltd Heat transfer structure
DE59709153D1 (de) 1997-07-03 2003-02-20 Alstom Switzerland Ltd Prallanordnung für ein konvektives Kühl-oder Heizverfahren
EP0892151A1 (fr) 1997-07-15 1999-01-20 Asea Brown Boveri AG Système de refroidissement pour le bord d'attaque d'une aube de turbine à gas
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DE10202783A1 (de) * 2002-01-25 2003-07-31 Alstom Switzerland Ltd Gekühltes Bauteil für eine thermische Maschine, insbesondere eine Gasturbine

Also Published As

Publication number Publication date
EP1959096A3 (fr) 2013-02-20
DE102007008319A1 (de) 2008-08-21
EP1959096A2 (fr) 2008-08-20
US8152463B2 (en) 2012-04-10
US20080226441A1 (en) 2008-09-18

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