EP0892150A1 - Kühlsystem für den Hinterkantenbereich einer hohlen Gasturbinenschaufel - Google Patents
Kühlsystem für den Hinterkantenbereich einer hohlen Gasturbinenschaufel Download PDFInfo
- 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
Links
Images
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)
Abstract
Description
- Fig. 1
- eine Schaufel im Querschnitt;
- Fig. 2
- den Hinterkantenbereich der Schaufel nach Fig. 1;
- Fig. 3
- einen Längsschnitt durch den Hinterkantenbereich;
- Fig. 4
- eine Variante der Rippenanordnung;
- Fig. 5
- das Detail z aus Fig. 1 mit einer zum Stand der Technik zählenden Hinterkante.
- a,b,c
- Innenkammern der Schaufel
- W
- Schaufelwand
- E
- Engspalt
- L
- Länge der Materialansammlung
- T
- Wandstärke
- d
- innere Kantenabrundung
- D
- äusseere Kantenabrundung
- 1
- Schaufelfuss
- 2
- Schaufelspitze
- 3
- längsdurchströmter Kanal
- 4
- Schaufelblatt
- 5
- Hinterkante
- 6
- Saugseite
- 7
- Druckseite
- 8,8'
- Rippe
- 9
- Steg
- h
- Höhe der Rippe
- H
- örtliche Breite des Kanals 3
Claims (8)
- Kühlsystem für den Hinterkantenbereich einer hohlen Gasturbinenschaufel, bei welcher sich vom Schaufelfuss (1) bis zur Schaufelspitze (2) ein längsdurchströmter Kanal (3) erstreckt, welcher im Bereich des Schaufelblattes (4) einerseits von den Innenwandungen der Hinterkante (5), der Saugseite (6) und der Druckseite (7) und andererseits von einem die Druckseite mit der Saugseite verbindenden Steg (9) begrenzt ist, wobei die Innenwandungen der Saugseite und der Druckseite mit einer Mehrzahl von zumindest annähernd parallel verlaufender Rippen (8) versehen sind,
dadurch gekennzeichnet, dass die Rippen (8) vom Steg (9) in Richtung Hinterkante (5) schräg verlaufen und an zumindest einer der beiden Innenwandungen radial auswärts gerichtet sind. - Kühlsystem nach Anspruch 1, dadurch gekennzeichnet, dass über der Schaufelhöhe die saugseitigen Rippen und die druckseitigen Rippen (um eine halbe Teilung) gegeneinander versetzt sind.
- Kühlsystem nach Anspruch 1, dadurch gekennzeichnet, dass die Höhe (h) der Rippen (8) von der Hinterkante (5) in Richtung Steg (9) zunimmt.
- Kühlsystem nach Anspruch 1, dadurch gekennzeichnet, dass das Verhältnis Höhe (h) der Rippen (8) zur örtlichen Höhe (H) des Kanals (4) über die Längserstreckung der Rippen konstant ist.
- Kühlsystem nach Anspruch 1, dadurch gekennzeichnet, dass die Höhe (h) der Rippen (8) im Bereich des Steges (9) abnimmt.
- Kühlsystem nach Anspruch 1, dadurch gekennzeichnet, dass die Höhe h der Rippen (8) über der Schaufelhöhe variabel ist.
- Kühlsystem nach Anspruch 1, dadurch gekennzeichnet,. dass die Teilung der Rippen (8) zueinander über der Schaufelhöhe variabel ist.
- Kühlsystem nach Anspruch 2, dadurch gekennzeichnet, dass die Rippen (8) an der Druckseite (7) vom Steg (9) in Richtung Hinterkante (5) radial auswärts gerichtet und die Rippen (8') an der Saugseite (6) vom Steg (9) in Richtung Hinterkante (5) radial einwärts gerichtet sind oder umgekehrt.
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 (de) | 1997-07-14 | 1997-07-14 | Kühlsystem für den Hinterkantenbereich einer hohlen Gasturbinenschaufel |
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 (de) | 1997-07-14 | 1997-07-14 | Kühlsystem für den Hinterkantenbereich einer hohlen Gasturbinenschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0892150A1 true EP0892150A1 (de) | 1999-01-20 |
EP0892150B1 EP0892150B1 (de) | 2003-02-05 |
Family
ID=8230297
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97810475A Expired - Lifetime EP0892150B1 (de) | 1997-07-14 | 1997-07-14 | Kühlsystem für den Hinterkantenbereich einer hohlen Gasturbinenschaufel |
Country Status (4)
Country | Link |
---|---|
US (1) | US6056508A (de) |
EP (1) | EP0892150B1 (de) |
JP (1) | JP4169834B2 (de) |
DE (1) | DE59709275D1 (de) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2001000965A1 (de) * | 1999-06-28 | 2001-01-04 | Siemens Aktiengesellschaft | Heissgasbeaufschlagbares bauteil, insbesondere turbinenschaufel |
WO2001071164A1 (de) * | 2000-03-22 | 2001-09-27 | Siemens Aktiengesellschaft | Versteifungs- und kühlstruktur einer turbinenschaufel |
EP1167690A1 (de) | 2000-06-21 | 2002-01-02 | Siemens Aktiengesellschaft | Kühlung der Abströmkante einer Gasturbinenschaufel |
US9388700B2 (en) | 2012-03-16 | 2016-07-12 | United Technologies Corporation | Gas turbine engine airfoil cooling circuit |
Families Citing this family (8)
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 |
CN117763763A (zh) * | 2024-01-02 | 2024-03-26 | 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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0130038A1 (de) * | 1983-06-20 | 1985-01-02 | General Electric Company | Turbulenzförderung |
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)
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 |
US4474532A (en) * | 1981-12-28 | 1984-10-02 | United Technologies Corporation | Coolable airfoil for a rotary machine |
US4775296A (en) * | 1981-12-28 | 1988-10-04 | 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 |
-
1997
- 1997-07-14 EP EP97810475A patent/EP0892150B1/de not_active Expired - Lifetime
- 1997-07-14 DE DE59709275T patent/DE59709275D1/de not_active Expired - Lifetime
-
1998
- 1998-07-08 US US09/111,778 patent/US6056508A/en not_active Expired - Lifetime
- 1998-07-13 JP JP19751098A patent/JP4169834B2/ja not_active Expired - Fee Related
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0130038A1 (de) * | 1983-06-20 | 1985-01-02 | General Electric Company | Turbulenzförderung |
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2001000965A1 (de) * | 1999-06-28 | 2001-01-04 | Siemens Aktiengesellschaft | Heissgasbeaufschlagbares bauteil, insbesondere turbinenschaufel |
US6641362B1 (en) | 1999-06-28 | 2003-11-04 | Siemens Aktiengesellschaft | Component that can be subjected to hot gas, especially in a turbine blade |
WO2001071164A1 (de) * | 2000-03-22 | 2001-09-27 | Siemens Aktiengesellschaft | Versteifungs- und kühlstruktur einer turbinenschaufel |
EP1167690A1 (de) | 2000-06-21 | 2002-01-02 | Siemens Aktiengesellschaft | Kühlung der Abströmkante einer Gasturbinenschaufel |
US9388700B2 (en) | 2012-03-16 | 2016-07-12 | United Technologies Corporation | Gas turbine engine airfoil cooling circuit |
Also Published As
Publication number | Publication date |
---|---|
JPH1172004A (ja) | 1999-03-16 |
US6056508A (en) | 2000-05-02 |
EP0892150B1 (de) | 2003-02-05 |
JP4169834B2 (ja) | 2008-10-22 |
DE59709275D1 (de) | 2003-03-13 |
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