EP0892150A1 - Système de refroidissement pour le bord de fuite des aubes creuses d'une turbine à gaz - Google Patents

Système de refroidissement pour le bord de fuite des aubes creuses d'une turbine à gaz Download PDF

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Publication number
EP0892150A1
EP0892150A1 EP97810475A EP97810475A EP0892150A1 EP 0892150 A1 EP0892150 A1 EP 0892150A1 EP 97810475 A EP97810475 A EP 97810475A EP 97810475 A EP97810475 A EP 97810475A EP 0892150 A1 EP0892150 A1 EP 0892150A1
Authority
EP
European Patent Office
Prior art keywords
ribs
height
web
blade
trailing edge
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
EP97810475A
Other languages
German (de)
English (en)
Other versions
EP0892150B1 (fr
Inventor
Prith Dr. Harasgama
Bruce Dr. Johnson
Bernhard Dr. Weigand
Pey-Chey Dr. Wu
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.)
General Electric Switzerland GmbH
Original Assignee
ABB Research Ltd Switzerland
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 ABB Research Ltd Switzerland filed Critical ABB Research Ltd Switzerland
Priority to DE59709275T priority Critical patent/DE59709275D1/de
Priority to EP97810475A priority patent/EP0892150B1/fr
Priority to US09/111,778 priority patent/US6056508A/en
Priority to JP19751098A priority patent/JP4169834B2/ja
Publication of EP0892150A1 publication Critical patent/EP0892150A1/fr
Application granted granted Critical
Publication of EP0892150B1 publication Critical patent/EP0892150B1/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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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 cooling system for the trailing edge area of a hollow Gas turbine blade, which extends from the blade root to the blade tip a longitudinally flowed channel extends in the area of the airfoil on the one hand from the inner walls of the rear edge, the suction side and the Pressure side and on the other hand from a connecting the pressure side with the suction side Web is limited, the inner walls of the suction side and the Printing page with a plurality of at least approximately parallel Ribs are provided.
  • the invention thus relates generally to a system for cooling a curved wall, which on one side of a hot medium and on a coolant flows around its other side.
  • Cooling poses a particular problem of the trailing edge area of such blades, which are in a closed circle are flowed through by the coolant.
  • the walls forming the rear edge include a narrow gap from which the heat is to be removed. For this, the Narrow gap in its width is not a minimal value for manufacturing reasons fall below. To avoid overheating the rear edge, you may also there are no large accumulations of material. In addition, the For strength reasons, the wall thickness should not fall below a certain dimension.
  • a cooling system of the type mentioned is known from DE-C2 32 48 162.
  • the area under consideration is equipped with ribs on its inner walls, which are parallel to the machine axis from the rear edge to the web. They are intended to trigger and promote turbulence.
  • the Rip a proper distance to the actual rear edge, which is therefore is rib-free.
  • These ribs have an axial extension constant height. Effective cooling of the actual rear edge area is done by blowing out the coolant via appropriately configured Elements.
  • the present invention has for its object a cooling system of the beginning to create the type mentioned, by increasing the turbulence in the Trailing edge area and other measures a considerable increase in Heat transfer coefficients can be achieved and heat dissipation is particularly improved from the existing narrow gap.
  • the new measure allows i.a. a formation of the trailing edge of the blade without Blow-out and thus allows the use of steam or others Media for cooling the blade.
  • the ratio of the height of the ribs to the local one Height of the canal increases from the rear edge towards the web or over the length of the ribs is constant.
  • This has the advantage that compared to the above State of the art, the trailing edge is subjected to greater pressure and at the same time the Web is relieved. The latter is important to avoid excessive tension on both sides Joints of the cool bar with the hot blade walls to avoid.
  • due to the rib configuration with constant local channel height ensures that fluid gets into the corner areas of the channel and there is a turbulent flow.
  • the ribs with constant local Channel height also ensure that a very strong secondary flow sets in, which is controlled by the large rib height in the free channel cross section becomes. This secondary flow takes warm fluid from the corner areas and supports the turbulent mixing in these areas.
  • a further relief of the web area is achieved when the height of the Ribs in the area of the web are reduced so early that the rib does not extends to the jetty or adjoins the jetty with a low height.
  • the turbulence then missing in this area advantageously reduces it Cooling of the web in the connection area.
  • the cast blade shown in Fig. 1 has three inner chambers a, b, and c on that of a coolant, such as steam, perpendicular to the plane of the drawing are flowed through.
  • a coolant such as steam
  • the inside of the blade contour forming wall W - which is surrounded on both sides by hot gases - by the Coolant flows around and give off their heat to the coolant.
  • Tools such as guide ribs, flow channels, inserts for impingement cooling and the like provided to improve wall cooling.
  • the coolant circulates in a closed circuit, which means that neither on the front edge, the suction side, the pressure side nor in the area of the Coolant is blown out of the trailing edge into the flow channel.
  • the problem with the actual trailing edge geometry is explained with reference to FIG. 5.
  • the gap E formed by the walls must have a minimum size in order to be able to absorb sufficient coolant to dissipate the heat generated.
  • the inner edge rounding must therefore be designed with the diameter d. This minimum diameter is usually determined by the manufacturing process, for example casting. For reasons of strength, a minimum wall thickness T cannot be exceeded either. In order to avoid overheating the rear edge, there must be no large accumulation of material there.
  • the dimension L a therefore generally corresponds to the wall thickness T. All of this means that the outer edge rounding must be carried out with a relatively large diameter D a . So far, cooled trailing edges are known.
  • FIGS. 2 and 3 show the cooling system for the trailing edge area of a hollow Gas turbine blade. It extends from the blade root 1 to the blade tip 2 a longitudinally flowed channel 3, which corresponds to the chamber c in Fig. 1. in the Area of the airfoil 4 is this channel from the inner walls of the Trailing edge 5, the suction side 6 and the pressure side 7 and the pressure side of one limited to the suction side connecting web 9.
  • the inner walls of the The suction side and the pressure side are inclined with a plurality and at least provided approximately parallel ribs 8, which are above the blade height are staggered.
  • the suction ribs and the pressure ribs are offset by half a pitch above the bucket height.
  • the ribs run radially outwards from the web 9 towards the rear edge an angle of 45 °. It is expected that the angle of attack is between 15 ° and 75 ° are suitable.
  • the effect of these inclined ribs is - in addition to the inherent, known function as a vortex generator - the following:
  • the rib structure creates a secondary flow in the duct, the warm air transported from the immediate area of the rear edge to the center of the channel. This warm air is replaced by colder air from the center of the duct.
  • the ratio of the height h of the ribs to the local height H of the channel 3 decreases from the rear edge 5 towards web 9.
  • This increase in height is in the Example chosen so that between the trailing edge and the web in each axial plane a freely flowed channel of approximately the same width is created. With this measure the coolant is evenly distributed over the entire flow Cross section reached. Only by introducing a location-dependent rib height are the two previously mentioned mechanisms for increasing heat transfer particularly effective.
  • the locally location-dependent rib height creates in Channel a flow that also flows into the narrow trailing edge area, since here the flow resistances are now about the same as in the rest of the canal.
  • the design of the new fins in the cooling passage also has a great impact positive and supportive of the above-mentioned secondary flow in the channel, which creates the air from the rear edge into the front channel area.
  • the high ribs in the front channel area induce a very strong one Secondary flow.
  • the height h of the individual ribs staggered above the blade height can of course be adapted to the local heat load.
  • a Enlargement of the ribs towards the tip of the blade is particularly then attached when the coolant passes through the channel has already warmed up strongly, so that with low rib height the required Temperature difference between the wall to be cooled and the coolant to the target Heat exchange no longer becomes smaller.
  • a variant is shown, in which also in the direction of the web widened ribs 8 on the pressure side 7 from the web 9 in the direction of the rear edge 5 directed radially outward and the ribs 8 'on the suction side 6 from the web in the direction Trailing edge are directed radially inwards.
  • This variant is considered based on the fact that more on the thermally more stressed blade side Heat must be dissipated if you are even in the rear edge area Metal temperatures above the profile circumference.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP97810475A 1997-07-14 1997-07-14 Système de refroidissement pour le bord de fuite des aubes creuses d'une turbine à gaz Expired - Lifetime EP0892150B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE59709275T DE59709275D1 (de) 1997-07-14 1997-07-14 Kühlsystem für den Hinterkantenbereich einer hohlen Gasturbinenschaufel
EP97810475A EP0892150B1 (fr) 1997-07-14 1997-07-14 Système de refroidissement pour le bord de fuite des aubes creuses d'une turbine à gaz
US09/111,778 US6056508A (en) 1997-07-14 1998-07-08 Cooling system for the trailing edge region of a hollow gas turbine blade
JP19751098A JP4169834B2 (ja) 1997-07-14 1998-07-13 中空のガスタービン羽根の後縁領域のための冷却装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810475A EP0892150B1 (fr) 1997-07-14 1997-07-14 Système de refroidissement pour le bord de fuite des aubes creuses d'une turbine à gaz

Publications (2)

Publication Number Publication Date
EP0892150A1 true EP0892150A1 (fr) 1999-01-20
EP0892150B1 EP0892150B1 (fr) 2003-02-05

Family

ID=8230297

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810475A Expired - Lifetime EP0892150B1 (fr) 1997-07-14 1997-07-14 Système de refroidissement pour le bord de fuite des aubes creuses d'une turbine à gaz

Country Status (4)

Country Link
US (1) US6056508A (fr)
EP (1) EP0892150B1 (fr)
JP (1) JP4169834B2 (fr)
DE (1) DE59709275D1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001000965A1 (fr) * 1999-06-28 2001-01-04 Siemens Aktiengesellschaft Composant, notamment aube de turbine, pouvant etre expose a un gaz chaud
WO2001071164A1 (fr) * 2000-03-22 2001-09-27 Siemens Aktiengesellschaft Structure de rigidification et de refroidissement d'une aube de turbine
EP1167690A1 (fr) 2000-06-21 2002-01-02 Siemens Aktiengesellschaft Refroidissement du bord de fuite d'une aube de turbine à gaz
US9388700B2 (en) 2012-03-16 2016-07-12 United Technologies Corporation Gas turbine engine airfoil cooling circuit

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7117686B2 (en) * 2003-12-11 2006-10-10 Utc Power, Llc High-efficiency turbulators for high-stage generator of absorption chiller/heater
US7513745B2 (en) * 2006-03-24 2009-04-07 United Technologies Corporation Advanced turbulator arrangements for microcircuits
US8246306B2 (en) * 2008-04-03 2012-08-21 General Electric Company Airfoil for nozzle and a method of forming the machined contoured passage therein
US8585365B1 (en) * 2010-04-13 2013-11-19 Florida Turbine Technologies, Inc. Turbine blade with triple pass serpentine cooling
JP6108982B2 (ja) * 2013-06-28 2017-04-05 三菱重工業株式会社 タービン翼及びこれを備える回転機械
JP6245740B2 (ja) * 2013-11-20 2017-12-13 三菱日立パワーシステムズ株式会社 ガスタービン翼
US10012092B2 (en) * 2015-08-12 2018-07-03 United Technologies Corporation Low turn loss baffle flow diverter
CN117763763B (zh) * 2024-01-02 2024-06-14 上海交通大学 用于角区流动控制的压气机叶根轴向非均匀倒圆优化方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0130038A1 (fr) * 1983-06-20 1985-01-02 General Electric Company Augmentation de la turbulence
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits

Family Cites Families (9)

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Publication number Priority date Publication date Assignee Title
GB1361256A (en) * 1971-08-25 1974-07-24 Rolls Royce Gas turbine engine blades
GB1410014A (en) * 1971-12-14 1975-10-15 Rolls Royce Gas turbine engine blade
US4775296A (en) * 1981-12-28 1988-10-04 United Technologies Corporation Coolable airfoil for a rotary machine
US4474532A (en) * 1981-12-28 1984-10-02 United Technologies Corporation Coolable airfoil for a rotary machine
US5232343A (en) * 1984-05-24 1993-08-03 General Electric Company Turbine blade
US5002460A (en) * 1989-10-02 1991-03-26 General Electric Company Internally cooled airfoil blade
US5695322A (en) * 1991-12-17 1997-12-09 General Electric Company Turbine blade having restart turbulators
US5488825A (en) * 1994-10-31 1996-02-06 Westinghouse Electric Corporation Gas turbine vane with enhanced cooling
US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0130038A1 (fr) * 1983-06-20 1985-01-02 General Electric Company Augmentation de la turbulence
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001000965A1 (fr) * 1999-06-28 2001-01-04 Siemens Aktiengesellschaft Composant, notamment aube de turbine, pouvant etre expose a un gaz chaud
US6641362B1 (en) 1999-06-28 2003-11-04 Siemens Aktiengesellschaft Component that can be subjected to hot gas, especially in a turbine blade
WO2001071164A1 (fr) * 2000-03-22 2001-09-27 Siemens Aktiengesellschaft Structure de rigidification et de refroidissement d'une aube de turbine
EP1167690A1 (fr) 2000-06-21 2002-01-02 Siemens Aktiengesellschaft Refroidissement du bord de fuite d'une aube de turbine à gaz
US9388700B2 (en) 2012-03-16 2016-07-12 United Technologies Corporation Gas turbine engine airfoil cooling circuit

Also Published As

Publication number Publication date
JP4169834B2 (ja) 2008-10-22
US6056508A (en) 2000-05-02
EP0892150B1 (fr) 2003-02-05
JPH1172004A (ja) 1999-03-16
DE59709275D1 (de) 2003-03-13

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