EP2087207A1 - Aube de turbine - Google Patents

Aube de turbine

Info

Publication number
EP2087207A1
EP2087207A1 EP07821492A EP07821492A EP2087207A1 EP 2087207 A1 EP2087207 A1 EP 2087207A1 EP 07821492 A EP07821492 A EP 07821492A EP 07821492 A EP07821492 A EP 07821492A EP 2087207 A1 EP2087207 A1 EP 2087207A1
Authority
EP
European Patent Office
Prior art keywords
ribs
cooling
turbine blade
pair
rib
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.)
Granted
Application number
EP07821492A
Other languages
German (de)
English (en)
Other versions
EP2087207B1 (fr
Inventor
Heinz-Jürgen GROSS
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 EP07821492.1A priority Critical patent/EP2087207B1/fr
Publication of EP2087207A1 publication Critical patent/EP2087207A1/fr
Application granted granted Critical
Publication of EP2087207B1 publication Critical patent/EP2087207B1/fr
Not-in-force 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
    • 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
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/181—Two-dimensional patterned ridged
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/34—Arrangement of components translated
    • 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
    • F05D2250/70—Shape
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a turbine blade.
  • Turbine blades particularly turbine blades for gas turbines, are exposed during operation to high temperatures which rapidly exceed the limit of material stress. This applies in particular to the areas in the vicinity of the flow inlet edge.
  • it has long been known to cool turbine blades suitable, so that they have a higher temperature resistance. With turbine blades, which have a higher temperature resistance, higher energy efficiencies can be achieved in particular.
  • Convection cooling is probably the most common type of blade cooling.
  • cooling air is passed through channels in the interior of the blade and uses the convective effect to dissipate the heat.
  • impingement cooling a cooling air flow bounces on the inside
  • the types of cooling described are suitably combined depending on the application in order to achieve the most effective blade cooling possible.
  • coolants such as turbulators, which are usually provided in the form of low ribs
  • the fins are disposed within the convection flow provided cooling channels that run inside the turbine blade.
  • the incorporation of fins in the cooling channels causes the flow of cooling air in the boundary layers to be detached and entangled. Due to the forced disruption of the flow, the heat transfer can be increased in the presence of a temperature difference between the cooling channel wall and the cooling air.
  • the ribbing constantly causes the flow to form new "recovery areas" in which a substantial increase in the local heat transfer coefficient can be achieved.
  • cooling channels are often formed in turbine blades parallel to and close to the flow inlet edge, to which cooling air is supplied by further cooling channels formed in the blades.
  • the thus realized convective cooling of the flow inlet edge is usually in film-sensed blades by a
  • Cooling arranged by on the inner wall of the cooling channel
  • the invention has for its object to provide a turbine blade whose flow inlet edge can be cooled more effectively compared to known solutions, both in existing as well as non-existing film cooling.
  • a turbine blade which has a plurality of ribs, which are arranged successively in a cooling channel which extends along a flow inlet edge, and in which each with two ribs a pair of ribs is formed, arranged the ribs in skating step shape are.
  • the inventively provided pairwise arrangement of the ribs in skate step shape causes over known solutions a greatly increased turbulence of the cooling air flowing in the cooling channel according to the invention, such that the cooling air flowing in the cooling channel from one rib of a rib-pair on the other rib of the ribs Pair is headed.
  • a greatly increased turbulence of the cooling air a greatly increased local heat transfer coefficient is connected, so that overall, compared to known solutions, a significantly more effective cooling, in particular in the region of the flow inlet edge, can be provided.
  • the turbine blade according to the invention can thus be exposed to higher gas temperatures, even if no film cooling is provided. If film cooling is provided, even higher gas temperatures are possible.
  • the two ribs of a rib pair are each designed as a guide element for a core flow of a cooling medium flowing in the cooling channel, such that the ribs guide the core flow from one rib of the rib pair substantially transversely to the other rib of the rib pair ,
  • a particularly large proportion namely the cooling medium flow flowing in the center of the duct, is guided as an impingement cooling jet against the side surfaces of the downstream ribs, so that in the region of the ribbed pair a very high local heat transfer coefficient and a According strong trained cooling effect can be achieved.
  • the ribs according to the invention are not turbulators in the sense of EP 1 637 699 A2, but guide elements with which a substantial proportion of the cooling medium can be deflected or diverted in each case.
  • the two ribs of a rib pair close a predetermined
  • Angle on, and a total cooling capacity of the two ribs of a rib-pair is adjusted over the angle of a predetermined cooling requirement for the flow inlet edge in the vicinity of the rib-pair.
  • the extent of turbulence of the cooling air and thus also the local heat transfer coefficient can be selectively influenced, so that a cooling adapted to a local cooling requirement for the flow inlet edge can be realized.
  • the cooling ability of a pair of ribs by increasing the angle of the two ribs of the rib-pair is included, be enlarged.
  • the temperature distribution at the flow inlet edge can be "made uniform" by means of this practical development, since according to the invention comparatively hot spots of the flow inlet edge by appropriately trained rib pairs a correspondingly strong cooling and vice versa, so that an effective cooling of the flow inlet edge can be realized which counteracts an inhomogeneous temperature distribution.
  • Flow inlet edge forms an inhomogeneous temperature distribution along the radial direction.
  • the ribs extend projecting from a wall bounding the cooling channel into the cooling channel, the ribs preferably being formed integrally with the bounding wall.
  • the rib pairs are mounted within an insert which is inserted into the cooling channel.
  • an insert is provided according to the invention, which can optionally be removed from the turbine blade, preferably in the form of a guide vane, to adapt, for example, the angular position of the rib pairs of a given application.
  • the casting of the turbine blade can also be kept simple, so that the turbine blade according to the invention can also be produced without elaborately designed casting cores.
  • the cooling channel extends parallel to the flow inlet edge continuously through the Turbine blade to provide effective cooling along the entire extent of the flow entry edge.
  • FIG. 2 shows a turbine blade with a cooling channel and arranged therein ribs
  • FIG. 3 shows a longitudinal section through the turbine blade along its flow inlet edge.
  • FIG. 1 shows a sketch-like sectional view of a turbine blade 10 according to the invention through its flow inlet edge 12.
  • the section according to the sectional surface AA of FIG. 1 is shown in FIG. 3, this being a sketch-like sectional view of the front section of a turbine blade 10 according to the invention.
  • a cooling channel 14 extending parallel to the flow inlet edge 12 is formed near the flow inlet edge 12 (ie a radially extending channel 14 in the case of axially through-flowed turbines).
  • a number of pairs of ribs 24 are arranged in succession in this, with the individual ribs 18 of each rib pair 24 being set transversely to each other by a predetermined angle ⁇ .
  • the ribs 18 of a pair of ribs 24, viewed along the cooling channel extension, are arranged offset to one another.
  • the ribs 18 of each pair 24 and the ribs 18 of immediately adjacent pairs 24 are thus arranged overlapping in skating step shape.
  • the ribs 18 according to the invention are designed as guide elements for the cooling air flowing in the center of the cooling channel 14 in order to mutually guide the substantial portion of the cooling air flowing there to the side surfaces of the following ribs 18. Accordingly, the ribs 18 according to the invention protrude substantially further into the cooling channel 18 than the turbulators of EP 1 637 699 A2, which, compared with the ribs 18, are only to be designated as near the surface and furthermore do not conduct or divert any significant portion of the cooling air.
  • the cooling air When flowing through the cooling channel 14, the cooling air is alternately deflected by the individual ribs 18 of each pair 24. A high degree of turbulence is formed at the bulging ribs 18, which flows in a transverse direction, which, in combination with impingement cooling effects and the associated cooling air-side surface enlargement, leads to an efficient use of cooling air.
  • the angle ⁇ in the central region of the turbine blade 10 is greater than in the edge regions of the turbine blade 10, so as to cool the middle, during operation usually strongly heated area of the flow inlet edge 12 stronger than the edge regions of the flow inlet edge 12 by an enlargement of the angle ⁇ , the cooling air is deflected more strongly, with a concomitant increased turbulence, which ultimately has a more pronounced increase in the local heat transfer coefficient compared to smaller angles.
  • the inhomogeneous temperature distribution that forms when the turbine blade 10 is used along the flow inlet edge 12 can be counteracted.
  • Suitable values for the angle ⁇ , which are adapted to the respective cooling requirement, according to the invention are in the range of about 60 ° to 90 °.
  • FIG. 2 the sketch-like sectional representation of the front section of the turbine blade 10 according to the invention is shown in FIG.
  • the individual ribs 18 of a pair 24 extend predominantly from a front wall 16 of the cooling channel 14 to a rear wall 20 of the cooling channel 14.
  • ribs 18 may be attached on one side only on the front wall 16, without extending to the rear wall 20.
  • the ribs may also be part of an insert which can be inserted in the cooling channel 14.
  • the cooling air can preferably be guided in the direction of the front wall 16 by suitably setting the angular position ⁇ , in order to achieve the most effective possible cooling of the flow inlet edge 12.
  • provided angular sizes are in the range of about 30 ° to 60 °.

Landscapes

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

Abstract

La présente invention concerne une aube de turbine (10) comprenant plusieurs nervures (18) qui sont disposées successivement dans un canal de refroidissement (14) qui s'étend le long d'un bord d'entrée de flux (12), deux nervures (18) formant respectivement une paire de nervures (24) dont les nervures (18) sont disposées en forme de pas de patineur.
EP07821492.1A 2006-11-09 2007-10-18 Aube de turbine Not-in-force EP2087207B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07821492.1A EP2087207B1 (fr) 2006-11-09 2007-10-18 Aube de turbine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06023377A EP1921269A1 (fr) 2006-11-09 2006-11-09 Aube de turbine
EP07821492.1A EP2087207B1 (fr) 2006-11-09 2007-10-18 Aube de turbine
PCT/EP2007/061127 WO2008055764A1 (fr) 2006-11-09 2007-10-18 Aube de turbine

Publications (2)

Publication Number Publication Date
EP2087207A1 true EP2087207A1 (fr) 2009-08-12
EP2087207B1 EP2087207B1 (fr) 2016-04-20

Family

ID=37909821

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06023377A Withdrawn EP1921269A1 (fr) 2006-11-09 2006-11-09 Aube de turbine
EP07821492.1A Not-in-force EP2087207B1 (fr) 2006-11-09 2007-10-18 Aube de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP06023377A Withdrawn EP1921269A1 (fr) 2006-11-09 2006-11-09 Aube de turbine

Country Status (4)

Country Link
US (1) US8215909B2 (fr)
EP (2) EP1921269A1 (fr)
JP (1) JP5329418B2 (fr)
WO (1) WO2008055764A1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120076660A1 (en) * 2010-09-28 2012-03-29 Spangler Brandon W Conduction pedestals for a gas turbine engine airfoil
US8920122B2 (en) 2012-03-12 2014-12-30 Siemens Energy, Inc. Turbine airfoil with an internal cooling system having vortex forming turbulators
WO2018153796A1 (fr) * 2017-02-24 2018-08-30 Siemens Aktiengesellschaft Pale ou aube de turbomachine ayant un canal de refroidissement avec un agencement croisé de broches
GB2574368A (en) * 2018-04-09 2019-12-11 Rolls Royce Plc Coolant channel with interlaced ribs
US10787932B2 (en) 2018-07-13 2020-09-29 Honeywell International Inc. Turbine blade with dust tolerant cooling system
US10669862B2 (en) * 2018-07-13 2020-06-02 Honeywell International Inc. Airfoil with leading edge convective cooling system
US10989067B2 (en) 2018-07-13 2021-04-27 Honeywell International Inc. Turbine vane with dust tolerant cooling system
GB201902997D0 (en) 2019-03-06 2019-04-17 Rolls Royce Plc Coolant channel
US11230929B2 (en) 2019-11-05 2022-01-25 Honeywell International Inc. Turbine component with dust tolerant cooling system

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Publication number Priority date Publication date Assignee Title
US4416585A (en) * 1980-01-17 1983-11-22 Pratt & Whitney Aircraft Of Canada Limited Blade cooling for gas turbine engine
JP3006174B2 (ja) * 1991-07-04 2000-02-07 株式会社日立製作所 内部に冷却通路を有する部材
US5695321A (en) * 1991-12-17 1997-12-09 General Electric Company Turbine blade having variable configuration turbulators
US5472316A (en) * 1994-09-19 1995-12-05 General Electric Company Enhanced cooling apparatus for gas turbine engine airfoils
DE19526917A1 (de) * 1995-07-22 1997-01-23 Fiebig Martin Prof Dr Ing Längswirbelerzeugende Rauhigkeitselemente
JP3396360B2 (ja) * 1996-01-12 2003-04-14 三菱重工業株式会社 ガスタービン冷却動翼
DE19634238A1 (de) * 1996-08-23 1998-02-26 Asea Brown Boveri Kühlbare Schaufel
US5797726A (en) * 1997-01-03 1998-08-25 General Electric Company Turbulator configuration for cooling passages or rotor blade in a gas turbine engine
EP0892149B1 (fr) * 1997-07-14 2003-01-22 ALSTOM (Switzerland) Ltd Système de refroidissement pour le bord d'attac d'une aube creuse pour turbine à gaz
EP1191189A1 (fr) * 2000-09-26 2002-03-27 Siemens Aktiengesellschaft Aube de turbine à gaz
US6742991B2 (en) * 2002-07-11 2004-06-01 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine
US7094031B2 (en) 2004-09-09 2006-08-22 General Electric Company Offset Coriolis turbulator blade
US8690538B2 (en) * 2006-06-22 2014-04-08 United Technologies Corporation Leading edge cooling using chevron trip strips
US20070297916A1 (en) * 2006-06-22 2007-12-27 United Technologies Corporation Leading edge cooling using wrapped staggered-chevron trip strips

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Also Published As

Publication number Publication date
US20100054952A1 (en) 2010-03-04
JP5329418B2 (ja) 2013-10-30
US8215909B2 (en) 2012-07-10
WO2008055764A1 (fr) 2008-05-15
EP2087207B1 (fr) 2016-04-20
EP1921269A1 (fr) 2008-05-14
JP2010509535A (ja) 2010-03-25

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