EP1584789B1 - Aube refroidie - Google Patents

Aube refroidie Download PDF

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Publication number
EP1584789B1
EP1584789B1 EP04008601A EP04008601A EP1584789B1 EP 1584789 B1 EP1584789 B1 EP 1584789B1 EP 04008601 A EP04008601 A EP 04008601A EP 04008601 A EP04008601 A EP 04008601A EP 1584789 B1 EP1584789 B1 EP 1584789B1
Authority
EP
European Patent Office
Prior art keywords
cooling channel
temperature
cooling
blade
dependent
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.)
Expired - Lifetime
Application number
EP04008601A
Other languages
German (de)
English (en)
Other versions
EP1584789A1 (fr
Inventor
Fathi Ahmad
Jürgen Dellmann
Heinz-Jürgen Dr. Gross
Andreas Dr. Kayser
Gernot Lang
Christian Menke
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.)
Siemens AG
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
Priority to EP04008601A priority Critical patent/EP1584789B1/fr
Priority to DE200450004022 priority patent/DE502004004022D1/de
Publication of EP1584789A1 publication Critical patent/EP1584789A1/fr
Application granted granted Critical
Publication of EP1584789B1 publication Critical patent/EP1584789B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50212—Expansivity dissimilar
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/505—Shape memory behaviour

Definitions

  • the invention relates to a blade, in particular a turbine blade with at least one cooling channel, z.
  • a guide or blade for a turbomachine.
  • the blade is, for example, in a turbomachine, for. B. in a gas turbine used.
  • a gas turbine is used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or blade rows, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium.
  • To guide the working fluid in the turbine unit also usually connected between adjacent blade rows are connected to the turbine housing Leitschaufelschschn.
  • the blades are thus exposed to high mechanical and thermal stresses. Therefore, they are usually cooled.
  • blades are highly idealized in design because the relatively large scatters in the blade manufacturing process can only be considered indirectly. As a result, an individual interpretation of the blade is limited.
  • the production-related variations in the design of the blades are compensated for example by a high cooling air requirement. This leads to a reduction in the efficiency of the associated gas turbine.
  • the cooling air supply for the blades is controlled by external throttle valves.
  • the throttle valves regulate the supply pressure and thus the amount of cooling air.
  • individual control of the amount of cooling air for each blade in a row of blades is not provided. Rather, the blades provided for an entire row are controlled via an associated common external throttle with regard to the amount of cooling air to be supplied. An individual control of the cooling of a single blade is not possible.
  • a turbine blade with a hollow blade is known, which is traversed by a coolant.
  • the coolant is supplied through a supply line to the closed-cooled airfoil and can flow off via a drain line.
  • a bimetallic strip is provided, which automatically closes both the inflow and outflow side of the orifices as a function of the temperatures of the turbine blade.
  • the invention is therefore based on the object to provide a blade, which has a comparison with the prior art, improved cooling.
  • the invention is based on the consideration that for a sufficiently long life of a blade production-related inaccuracies in the manufacture of the turbine blades should be compensated during operation of the blade.
  • a uniform stress field distribution of the blade should be ensured during operation of a turbine.
  • the amount of cooling medium guided through the blade should be dependent on the temperature level within the blade.
  • the cooling channel is designed such that the coolant channel flowing through the cooling medium quantity is temperature-dependent controllable.
  • the guided through the cooling channel cooling medium quantity is dependent on the cross-sectional size of the cooling channel.
  • the cross-section of the cooling channel therefore expediently varies, depending on the temperature, at least regionally, in particular in the flow inlet region, in the flow outlet region and / or in the channel region.
  • sections by corresponding temperature-dependent configuration of the cooling channel enlargement and / or reduction of the cross section of the cooling channel can be effected
  • the invention provides for a varying cross-section of the cooling channel that it is provided with at least two layers at least partially surrounding the cooling channel wall.
  • the layers of different temperature-dependent material are formed in the manner of a bi-metal strip.
  • one of the layers of a solid as possible, especially temperature-resistant material and the other layer is formed of a soft, temperature dependent material.
  • As a possible material for the coating of the cooling channel wall for example, steel of different hardness with different coefficients of expansion and different modulus of elasticity is used.
  • the layers can be formed as full or partial layers.
  • the coating of the cooling channel wall is preferably provided in a widened region, in particular in a widened flow input or flow output region.
  • the cooling channel wall in the flow inlet region in the blade root is widened conically and provided with at least two layers. Due to the temperature acting on the blade, the respective layer of the temperature-dependent material then experiences an expansion or shrinkage, which leads to a narrowing or a change in the cross section of the cooling channel, so that a throttle point is formed in the cooling channel.
  • the cooling channel which varies in cross-section, it is provided with at least one temperature-dependent throttling point varying in cross-section.
  • the throttle point is formed in an additionally expanded flow inlet region and / or flow outlet region of the cooling channel.
  • the cooling channel is provided with a throttle element in the area of the throttle point.
  • a throttle element projects horizontally into the cooling channel via an opening arranged in the cooling channel wall.
  • the throttle element is formed, for example, pin-like.
  • the throttle element is made of a bi-metal material.
  • the throttle element is designed as an orifice.
  • the orifice plate comprises a plurality of bi-metal sector plates with different staggered temperature application points.
  • the throttle element is designed as a disk throttle.
  • the throttle element comprises a ring arranged on the cooling channel wall, on which fins are arranged.
  • the throttle element may be formed by a plurality of the cooling channel wall encircling ring segments with lamellae.
  • the ring can be arranged fixed or freely movable on the cooling channel wall.
  • the slats can be arranged in pairs, for example. Depending on the specification of the throttle effect at the relevant point in the cooling channel beyond the slats can be arranged fixed or freely movable.
  • a throttle element is given by a throttle plate, which is arranged perpendicular to the cooling channel axis in the cooling channel.
  • the throttle element in particular the throttle plate, at least partially disposed along the cooling channel wall.
  • the throttle plate protrudes at least partially out of the cooling channel opening in the form of a collar.
  • the throttle plate is formed for example as an L-profile, whose long leg is arranged in the cooling channel and whose short leg at least partially forms the edge of the cooling channel opening.
  • the throttle plate is at least partially, in particular in the region of the protruding into the cooling channel long leg formed as a bi-metal strip. As a function of the temperature of the cooling medium flowing through in the area of the bi-metal strip, the bi-metal strip expands, as a result of which the throttle plate is displaced such that the cooling channel opening is at least partially closed or opened.
  • z. B type of material of the throttle element or its arrangement in the cooling channel, takes place at the throttle point, a change in cross section by expansion or shrinkage in a range of 0% to 30%, in particular from 10% to 20%, the cross-sectional size of the cooling channel.
  • the advantages achieved by the invention are in particular that with a temperature-dependent throttling in the cooling channel of a respective blade by appropriate design of the cooling channel itself, being closed or opened with increasing heating of the cooling channel with respect to the amount of cooling medium flowing through, the consumption of cooling medium, eg. B. cooling or compressor air is limited without a design change or design to the current thermal state of the blade and thus the cooling is optimized.
  • cooling medium eg. B. cooling or compressor air
  • the blade is exposed to less thermal stress by reducing the temperature gradients.
  • the efficiency of a turbine can be raised in the design point by optimized cooling medium requirement without safety margin against overheating.
  • FIG. 1 shows a blade 1, z. B. a turbine blade, in particular a rotor or vane.
  • the blade 1 is provided for the purpose of cooling with a plurality of cooling channels 2, which in a manner not shown vertically and / or horizontally, looped and / or can extend largely straight through the blade 1. Depending on the function of the respective cooling channel 2, this has a corresponding diameter D.
  • the cooling channels 2 shown vertically are formed with a larger diameter D, since these cooling channels 2 are mostly used as so-called main cooling channels or collecting cooling channels.
  • the blade 1 in a particularly hot acted upon area a plurality of cooling channels 2 and less hot areas acted upon a smaller number of cooling channels 2, as shown in FIG.
  • the cooling channel 2 in a particularly hot acted upon area, for. B. in the region of a leading edge 3 of the blade 1, a cooling channel 2 with a particularly large diameter D, z. B. from 3 mm to 4 mm, in particular of 3.3 mm, whereas in a not so hot acted area, the cooling channels 2 have a smaller diameter D, as shown for example in FIG.
  • the cooling channel 2 is designed such that the coolant channel 2 flowing through the cooling medium quantity is temperature-dependent controllable. This is achieved by controlling the amount of cooling medium guided through the cooling channel 2 as a function of the cross-sectional size of the cooling channel 2.
  • this is in a first possible embodiment with at least two the cooling channel wall 4, d. H. the inner wall, provided at least partially circumferential layers S1 and S2.
  • the layers S1 and S2 are formed of different temperature-dependent material in the manner of a bi-metal strip.
  • one of the layers S2 is formed from a material which is as strong as possible, in particular temperature-resistant, and the other layer S1 from a soft, temperature-dependent material.
  • the temperature-stable layer S2 is the outer layer and the inner wall of the cooling channel 2 forming layer.
  • the temperature-dependent layer S1 is arranged between the layer S1 and the base material G of the blade 1. It is also possible to provide further layers Sn, which are formed from the same or different material.
  • the respective layer S1 and S2 in the normal state have a thickness of 0.1 mm to 0.7 mm, in particular from 0.1 mm to 0.3 mm.
  • the layers S1 and S2 may be formed as full or partial layers.
  • the cross section of the cooling channel 2 varies depending on the temperature T, in particular of temperature changes .DELTA.T.
  • the cooling channel 2 is provided, for example, in the flow input region, in the flow outlet region and / or in the channel region with the layers S1 and S2.
  • the layers S1, S2 formed from different temperature-dependent material make it possible to have a cooling channel 2 which varies in cross section, the layers S1, S2 forming at least one temperature-dependent throttle point 6 varying in cross-section in the cooling channel 2. 4 and 5, the cooling channel 2 is shown in longitudinal section in the region of a throttle point 6 formed by the layers S1 and S2.
  • the cooling channel 2 can be provided in regions along its longitudinal orientation with the layers S1 and S2. Due to the generally small cross-sectional sizes of the cooling channels 2 of a blade 1, the coating of the cooling channel wall 4 is preferably arranged in a widened region of the cooling channel 2, in particular in a widened flow input or flow output region. For example, the cooling channel wall 4 in the flow inlet region in the blade root is widened conically and provided with at least two layers S1, S2. Due to the temperature acting on the blade 1, the layer S1 then experiences a shrinkage from the temperature-dependent material (see FIG. 4) or expansion (see FIG.
  • FIG. 5 the cooling channel 2 of the blade 1 is shown in the state at cold temperatures with an associated diameter Dc
  • FIG. 5 the cooling channel 2 is in the state when the blade 1 is acted upon hot temperatures with an associated large diameter Dh, where: Dc ⁇ Dh.
  • z. B. type of material or its arrangement in the cooling channel 2 takes place at the throttle point 6, a change in cross section by expansion or shrinkage in a range of 0% to 30%, in particular from 10% to 20%, the cross-sectional size of the cooling channel. 2
  • the cooling channel 2 is provided with a throttle element 8 in the region of the throttle point 6.
  • the throttle element 8 projects horizontally into the cooling passage 2 via an opening 10 arranged in the cooling passage wall 4.
  • the throttle element 8 is formed, for example, pin-like.
  • the throttle element 8 is made of a bi-metal material.
  • FIGS. 7A, 7B and 8A, 8B show another embodiment not according to the invention for a throttle point 6 in the cooling channel 2.
  • FIGS. 7A, 7B show the cooling channel 2 in the area of the throttle point 6 and the blade 1 with hot temperatures T and a correspondingly large diameter D for the greatest possible flow through the cooling channel 2 with the cooling medium in the flow direction P2.
  • FIGS. 8A, 8B show the cooling channel 2 in the region of the throttle point 6 in the normal state, ie at cold temperatures T, so that the cooling channel 2 has a small diameter D with a correspondingly smaller channel cross section.
  • 7A shows the cooling channel 2 in cross section, d. H. in the wide open state with the largest possible diameter D, so that a corresponding maximum amount of cooling air flows through the cooling channel 2.
  • 7B shows the cooling channel 2 according to FIG. 7A in a longitudinal section in the area of the throttle point 6, wherein a throttle plate 10 is provided as throttle element 8, which is arranged perpendicular to the cooling channel axis in the cooling channel 2.
  • the throttle plate 10, which is formed for example as a perforated plate, is arranged at least partially along the cooling channel wall 4.
  • the throttle plate 10 projects at least partially out of a cooling channel opening 12 in the form of a collar.
  • the throttle plate 12 is formed, for example, as an L-profile, whose long leg is disposed in the cooling channel 2 and whose short leg at least partially forms the edge of the cooling channel opening 12.
  • the throttle plate 10 is formed at least partially, in particular in the region of the projecting into the cooling channel 2 long leg as bi-metal strips 10a, 10b.
  • a bi-metal strip 10a, 10b By using a bi-metal strip 10a, 10b, a temperature-dependent individual control of the amount of cooling air for each blade 1 can be achieved.
  • the bi-metal strip 10a, 10b expands, causing the throttle plate 10 to be displaced such that the cooling channel opening 12 is at least partially closed (FIGS. 8A, 8B) or completely open (FIGS. 7A, 7B).
  • FIGS. 9 and 10 show another embodiment not according to the invention for a throttle element 8 designed as a throttle plate 10.
  • the cooling channel 2 passes through the blade 1 with a curved course, wherein the cooling channel 2 is divided into branch channels by the throttle element 8 formed by two throttle plates 10.
  • the throttle plates 10 are made of a temperature-dependent material with a high expansion coefficient. By using such throttle plates 10, a temperature-dependent individual control of the amount of cooling air for the individual blade 1 is effected. Depending on the temperature change .DELTA.T between the blade 1 and throttle plate 10, a more or less large gap S is released, which controls the amount of cooling air.
  • FIG. 10 shows another embodiment of the invention for a throttle plate 10 with a bi-metal strip 10a, 10b extending along the channel wall 4, which causes opening and closing of the cooling channel opening 12, as in FIGS. 7A to 8B.
  • the bi-metal strip 10a, 10b has differently staggered temperature application points.
  • the throttle element 8 is formed as a disk throttle 14, as shown in FIG 11.
  • the throttle element 8 comprises a arranged on the cooling channel wall 4 ring R, on which slats L are arranged.
  • the throttle element 8 may be formed of several, the cooling channel wall 4 encircling ring segments RS with lamellae L, as shown in Figures 12 and 13.
  • the ring R or the ring segments RS can be arranged fixed or freely movable on the cooling channel wall 4.
  • one of the rings can be fixed and the other ring can be freely moved.
  • the lamellae L can be arranged in pairs, for example.
  • the slats L can be arranged fixed or freely movable.
  • FIGS. 14A and 14B show another embodiment not according to the invention for a throttle point 6 with a throttle element 8, which is designed as an orifice plate 14.
  • the orifice 14 is formed of a plurality of bi-metal sector plates 14a to 14d having different staggered temperature application points.
  • a throttling of the cooling channel 2 flowing through the amount of cooling air is effected, which is temperature-dependent by changing the position of the bi-metal sector plates 14a to 14d.
  • the consumption of cooling air without a design allowance is limited to the current thermal state of the blade 1 and the cooling of the blade 1 optimized.

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

Claims (8)

  1. Aube (1) ayant au moins un canal (2) de refroidissement qui débouche côté sortie du courant dans un espace environnant, le canal (2) de refroidissement étant tel qu'une quantité du fluide de refroidissement passant dans le canal (2) de refroidissement peut être réglée en fonction de la température et la section transversale du canal (2) de refroidissement peut être modifiée au moins par endroit en fonction de la température,
    le canal (2) de refroidissement étant muni en au moins un point (6) d'étranglement d'un élément (8) d'étranglement variable en fonction de la température (T) du fluide de refroidissement,
    caractérisée en ce que
    le canal (2) de refroidissement est muni d'au moins deux couches (S1, S2) faisant le tour au moins en partie de la paroi (4) du canal de refroidissement.
  2. Aube suivant la revendication 1,
    dans laquelle le point (6) d'étranglement est formé dans une partie d'entrée du courant et/ou dans une partie de sortie du courant du canal (2) de refroidissement élargie supplémentairement.
  3. Aube suivant l'une des revendications 1 ou 2,
    dans laquelle l'élément (8) d'étranglement est constitué sous la forme d'un diaphragme (14) d'étranglement.
  4. Aube suivant l'une des revendications 1, 2 ou 3,
    dans laquelle les couches (S1, S2) sont en un matériau différent en fonction de la température à la façon d'un bilame (10a, 10b).
  5. Aube suivant l'une des revendications 1 à 4,
    dans laquelle l'une des couches (S1) est en un matériau aussi solide que possible, notamment en un matériau stable à la température, et l'autre couche (S2) est en un matériau qui se modifie en fonction de la température.
  6. Aube suivant la revendication 5,
    dans laquelle le matériau stable en fonction de la température est formée d'une tôle, notamment d'acier, ayant un petit coefficient de dilatation.
  7. Aube suivant la revendication 5 ou 6,
    dans laquelle le matériau qui varie en fonction de la température est formé d'une tôle, notamment en acier, ayant un grand coefficient de dilatation (αsg).
  8. Aube suivant l'une des revendications 1 à 7,
    dans laquelle chaque couche (S1, S2) a à l'état normal une épaisseur de 0,1 mm à 0,7 mm, notamment de 0,1 mm à 0,3 mm.
EP04008601A 2004-04-08 2004-04-08 Aube refroidie Expired - Lifetime EP1584789B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP04008601A EP1584789B1 (fr) 2004-04-08 2004-04-08 Aube refroidie
DE200450004022 DE502004004022D1 (de) 2004-04-08 2004-04-08 Kühlbare Schaufel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04008601A EP1584789B1 (fr) 2004-04-08 2004-04-08 Aube refroidie

Publications (2)

Publication Number Publication Date
EP1584789A1 EP1584789A1 (fr) 2005-10-12
EP1584789B1 true EP1584789B1 (fr) 2007-06-06

Family

ID=34896038

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04008601A Expired - Lifetime EP1584789B1 (fr) 2004-04-08 2004-04-08 Aube refroidie

Country Status (2)

Country Link
EP (1) EP1584789B1 (fr)
DE (1) DE502004004022D1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015112268A3 (fr) * 2013-12-16 2015-10-15 United Technologies Corporation Modulation de refroidissement de profil aérodynamique centrifuge

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Publication number Priority date Publication date Assignee Title
JP5350366B2 (ja) 2007-05-17 2013-11-27 エネロ インヴェンションズ 即時応答蒸気発生システム及び方法
FR2916475B1 (fr) * 2007-05-23 2009-10-16 Snecma Sa Circuit d'alimentation en air de ventilation d'un rotor de turbine dans un moteur a turbine a gaz
US9261022B2 (en) * 2012-12-07 2016-02-16 General Electric Company System for controlling a cooling flow from a compressor section of a gas turbine
WO2014143236A1 (fr) * 2013-03-15 2014-09-18 Duge Robert T Système de refroidissement d'aube de turbine, moteur à turbine à gaz et procédé d'actionnement correspondants
US9845731B2 (en) * 2014-09-24 2017-12-19 United Technologies Corporation Self-modulated cooling on turbine components
EP3147455A1 (fr) * 2015-09-23 2017-03-29 Siemens Aktiengesellschaft Aube directrice de turbine ayant un agencement d'étranglement
US10113441B2 (en) 2016-01-07 2018-10-30 United Technologies Corporation Thermally driven spring valve for turbine gas path parts

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Publication number Priority date Publication date Assignee Title
US2977090A (en) * 1956-06-12 1961-03-28 Daniel J Mccarty Heat responsive means for blade cooling
US4751962A (en) * 1986-02-10 1988-06-21 General Motors Corporation Temperature responsive laminated porous metal panel
US5022817A (en) * 1989-09-12 1991-06-11 Allied-Signal Inc. Thermostatic control of turbine cooling air
GB2354290B (en) * 1999-09-18 2004-02-25 Rolls Royce Plc A cooling air flow control device for a gas turbine engine
DE10225264A1 (de) * 2001-09-17 2003-04-03 Alstom Switzerland Ltd Luftgekühlte Turbinenschaufel mit Deckbandelement
DE10202783A1 (de) * 2002-01-25 2003-07-31 Alstom Switzerland Ltd Gekühltes Bauteil für eine thermische Maschine, insbesondere eine Gasturbine

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Title
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015112268A3 (fr) * 2013-12-16 2015-10-15 United Technologies Corporation Modulation de refroidissement de profil aérodynamique centrifuge
US10273809B2 (en) 2013-12-16 2019-04-30 United Technologies Corporation Centrifugal airfoil cooling modulation
US10844730B2 (en) 2013-12-16 2020-11-24 United Technologies Corporation Centrifugal airfoil cooling modulation

Also Published As

Publication number Publication date
EP1584789A1 (fr) 2005-10-12
DE502004004022D1 (de) 2007-07-19

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