EP0892150B1 - 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
EP0892150B1
EP0892150B1 EP97810475A EP97810475A EP0892150B1 EP 0892150 B1 EP0892150 B1 EP 0892150B1 EP 97810475 A EP97810475 A EP 97810475A EP 97810475 A EP97810475 A EP 97810475A EP 0892150 B1 EP0892150 B1 EP 0892150B1
Authority
EP
European Patent Office
Prior art keywords
ribs
blade
height
trailing edge
web
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
EP97810475A
Other languages
German (de)
English (en)
Other versions
EP0892150A1 (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
Alstom Schweiz 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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
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 Print 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 is 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 below. To avoid overheating the rear edge, you may also there are no large accumulations of material. In addition, the For reasons of strength, 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, that run 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 carried out by blowing out the coolant via appropriately configured Elements.
  • the ribs are in the generic cooling system according to US 5634766 arranged inclined to the machine axis, in such a way that the ribs on the opposite inner walls of pressure and Suction side are aligned opposite, that is, radially outward arranged ribs on the suction side are radially inwardly directed ribs of the Print side opposite or vice versa.
  • This arrangement is said to more uniform application across the entire cross-section of the rear Blade cavity can be achieved with a turbulent coolant flow. But even after this proposed solution, the effective cooling of the actual trailing edge of the blade by blowing out the turbulent coolant. In addition, the trailing edge area is additionally cooled by means of film protected.
  • the present invention has for its object to provide a cooling system of the type mentioned, in which a significant increase in the heat transfer coefficient can be achieved by increasing the turbulence in the trailing edge area and other measures, and the heat dissipation from the existing narrow gap, especially in such blades, through which coolant flows in a closed circuit is improved.
  • the new measure allows i.a. a formation of the blade trailing edge 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.
  • a further relief of the web area is achieved when the height of the Ribs in the area of the web are reduced early so that the ribs do not go up enough to the jetty or adjoining the jetty with only a low height.
  • the then lack of turbulence in this area causes an advantageous reduced 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 6 and the pressure side 7 are inclined and at least with a plurality 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 over the blade height.
  • the ribs run radially outwards from the web 9 towards the rear edge at 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 - besides that Inherent, known function as a vortex generator - the following:
  • the rib structure causes a secondary flow in duct 3, 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 staggered arrangement of the ribs on the suction side 6 and the pressure side 7 does the following:
  • 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 there is a free space between the rear edge and the web in each axial plane flowed channel is about the same width. With this measure a uniform coolant distribution 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 approximately 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 ribs 8 increases in the area of the web 9 steadily towards zero. It goes without saying that, due to the manufacturing process, sharp-edged Connections are hardly possible. As already mentioned, this configuration has the advantage that at the junction of the web with the inner walls the coolant flows along the walls almost without interference and thus less cooling effect developed. Of course, the intermediate bridge 9 may never get too hot. Should this be due to the selected configuration can occur, there is easily the possibility of the ribs up to Continuing the web with an adjusted height, i.e. with the same or reduced Height.
  • 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.
  • Fig. 4 a variant is shown, in which the web 9 also in the direction widened ribs 8 on the pressure side 7 from the web 9 in the direction of the rear edge 5 directed radially outwards 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.

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

Claims (7)

  1. Système de refroidissement pour la zone du bord arrière d'une pale creuse de turbine à gaz dans laquelle un canal (3) traversé longitudinalement par un écoulement s'étend depuis le pied de pale (1) jusqu'à la pointe de pale (2) et est délimité dans la zone de la feuille de pale (4) d'une part par les parois intérieures du bord arrière (5), celles du côté aspiration (6) et celles du côté refoulement (7), et d'autre part par une traverse (9) qui relie le côté refoulement au côté aspiration, les parois intérieures du côté aspiration et du côté refoulement étant dotées d'une pluralité de nervures (8) qui s'étendent au moins approximativement en parallèle, lesquelles nervures (8) s'étendent obliquement depuis la traverse (9) en direction du bord arrière (5) et sont orientées radialement vers l'extérieur et vers au moins l'une des deux parois intérieures, caractérisé en ce que la hauteur (h) des nervures (8) augmente depuis le bord arrière (5) en direction de la traverse (9).
  2. Système de refroidissement selon la revendication 1, caractérisé en ce que le rapport entre la hauteur (h) des nervures (8) et la hauteur locale (H) du canal (4) est constant sur toute l'extension longitudinale des nervures.
  3. Système de refroidissement selon la revendication 1, caractérisé en ce que la hauteur (h) des nervures (8) diminue dans la région de la traverse (9).
  4. Système de refroidissement selon la revendication 1, caractérisé en ce que la hauteur (h) des nervures (8) varie en fonction de la hauteur de la pale.
  5. Système de refroidissement selon la revendication 1, caractérisé en ce que la répartition des nervures (8) les unes par rapport aux autres varie en fonction de la hauteur de la pale.
  6. Système de refroidissement selon la revendication 1, caractérisé en ce que les nervures (8') situées du côté aspiration et les nervures (8) situées du côté refoulement sont décalées les unes par rapport aux autres d'un demi-intervalle sur la hauteur de la pale.
  7. Système de refroidissement selon la revendication 6, caractérisé en ce que sur le côté refoulement (7), les nervures . (8) sont orientées radialement vers l'extérieur depuis la traverse (9) et en direction du bord arrière (5), et en ce que sur le côté aspiration (6), les nervures (8') sont orientées radialement vers l'intérieur depuis la traverse (9) et en direction du bord arrière (5).
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 EP0892150A1 (fr) 1999-01-20
EP0892150B1 true EP0892150B1 (fr) 2003-02-05

Family

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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)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4489336B2 (ja) * 1999-06-28 2010-06-23 シーメンス アクチエンゲゼルシヤフト 高温ガスを受ける構造部品
DE50105063D1 (de) * 2000-03-22 2005-02-17 Siemens Ag Versteifungs- und kühlstruktur einer turbinenschaufel
EP1167690A1 (fr) 2000-06-21 2002-01-02 Siemens Aktiengesellschaft Refroidissement du bord de fuite d'une aube de turbine à gaz
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
US9388700B2 (en) 2012-03-16 2016-07-12 United Technologies Corporation Gas turbine engine airfoil cooling circuit
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

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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
US4514144A (en) * 1983-06-20 1985-04-30 General Electric Company Angled turbulence promoter
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
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
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

Also Published As

Publication number Publication date
EP0892150A1 (fr) 1999-01-20
US6056508A (en) 2000-05-02
JP4169834B2 (ja) 2008-10-22
JPH1172004A (ja) 1999-03-16
DE59709275D1 (de) 2003-03-13

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