EP0182588B1 - Mehrkammereinsatz zur Kühlung einer Turbinenschaufel - Google Patents

Mehrkammereinsatz zur Kühlung einer Turbinenschaufel Download PDF

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Publication number
EP0182588B1
EP0182588B1 EP85308230A EP85308230A EP0182588B1 EP 0182588 B1 EP0182588 B1 EP 0182588B1 EP 85308230 A EP85308230 A EP 85308230A EP 85308230 A EP85308230 A EP 85308230A EP 0182588 B1 EP0182588 B1 EP 0182588B1
Authority
EP
European Patent Office
Prior art keywords
chambers
rearward
turbine
insert
ports
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
Application number
EP85308230A
Other languages
English (en)
French (fr)
Other versions
EP0182588A1 (de
Inventor
Thomas M. Szewczuk
William Edward North
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.)
CBS Corp
Original Assignee
Westinghouse Electric Corp
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 Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Publication of EP0182588A1 publication Critical patent/EP0182588A1/de
Application granted granted Critical
Publication of EP0182588B1 publication Critical patent/EP0182588B1/de
Expired 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
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • This invention relates to a combustion turbine and in particular to an airfoil-shaped, hollow turbine vane having a leading edge wall.
  • Such turbine airfoil vanes provided with an insert, with the arrangement as a whole providing for air cooling of the vanes.
  • the vane structure is of a character and in a stage calling for a low or a moderate level of cooling, which level of cooling can be carried out by the use of impingement jets directed against the interior walls of the vane. Even with those vanes which do not require a high level of cooling, the degree of cooling required at different locations on the vane may differ, with the leading edge region of the vane typically having a relatively higher heat load while downstream and toward the trailing edge of the vane the heat load may be significantly lower.
  • French Patent No. 2,457,965 discloses turbine blades with inserts defining a front chamber to which a cooling gas is supplied and escapes partially through passages in the leading edge of the blade and partially into a space between the insert in the front chamber and the blade wall. The cooling gas then enters the interior of an insert in the rear chamber from where the cooling gas is discharged through openings therein into a space formed between the insert and the blade walls before it is discharged through openings in the trailing edge of the blade.
  • U.S. Patent 2,873,944 also discloses turbine blades or vanes with cooling air guide inserts defining different chambers provided with openings for even distribution of the cooling air to the inner surfaces of the blade or vane walls.
  • the present invention resides in a combustion turbine with airfoil-shaped, hollow, turbine vanes having leading edge walls, trailing edge portions with exit air slots therein, and pressure and suction sidewalls defining internal cavities in communication with said exit air slots, with hollow inserts of substantially complementary airfoil shape in cross section located in said cavities and extending in a chordwise direction for substantially the entire extent of said cavities in spaced relationship from the walls thereof, characterized in that said inserts are single unitary structures with a plurality of radially extending partitions in each insert dividing the interior thereof into a forward chamber in the leading edge portion of said vane, and at least two separate, successively rearward chambers in communication with each other, a plurality of impingement ports in the insert walls of all of the said chambers, one radial end portion of said chambers being in communication with a source of cooling air, and that for throttling the flow into said rearward chambers are provided such that said forward chamber is at a relatively higher pressure than said rearward chambers and the imp
  • the single, unitary, air-cooling, hollow insert 22 has an airfoil shape in cross section which is complementary to the vane airfoil shape, and extends in a chordwise direction for substantially the entire extent of the vane cavity. While the insert does have the overall shape of an airfoil, it may be seen in Figure 1 that at the leading edge portion 24 the insert is bulged somewhat, a similar bulged arrangement being provided at the trailing edge portion 26.
  • the intermediate portion 28 has walls which are basically uniformly spaced from the vane wails throughout the intermediate extent between the front and rear bulges.
  • the unitary insert 22 has its interior divided into a forward chamber 30 and successively rearward chambers 32, 34, and 36, by the radially-extending partition means 38, 40, and 42, which also perform a structural tying function.
  • the radially inner ends of all of the chambers are closed while the radially outer ends of the chambers are in communication with a source of cooling air.
  • the radially outer end 44 is completely open so that cooling air flows directly into the forward chamber 30 as indicated by the arrow 46 in Figure 2.
  • the flow into these chambers is throttled by means of a radial extension 48 of the insert comprising opposite walls 50 capped by plate 52 which prevents the direct admission of the cooling air into the rearward chambers in the fashion in which the forward chambers receives its air, the cooling air being throttled into the rearward chambers by the provision of the holes 54 in the walls 50.
  • the throttling results in the rearward chambers being at a lower pressure than the forward chamber 30.
  • all of the chambers are provided with impingement ports in their sidewalls.
  • Those ports provided in the forward chamber sidewalls are identified by the numeral 56 as best seen in Figre 1.
  • the impingement ports in the convex sidewall of the insert for the rearward chambers are designated 58 while those in the concave wall are designated 60.
  • All of the impingement ports are in rows which extend substantially radially.
  • the rows of ports 56 of the forward chamber are more widely spaced from each other than the rows of ports from-the rearward chambers on the convex side, and most of the concave side with the exception of the spacing of the rows of ports of the concave side of the first low-pressure chamber 32.
  • the three rearward chambers are open to each other through the provision of a series of ports 62 in both of the partitions or ribs 40 and 42.
  • the rearward chambers are also in open communication with each other at the radially outer portion of the chambers by virtue of the partitions 40 and 42 stopping short of the space 64 at the radially outer ends of the chambers.
  • the insert has dimples 66 embossed outwardly in its leading edge portion and similar dimples 68 in its trailing edge portion to properly space the insert walls from the vane walls.
  • the forward chamber 30 is maintained at a higher pressure than the rearward chambers 32, 34, and 36, so that the cooling jets issuing from the forward chamber are projected at a higher velocity than those exiting through the ports of the rearward chambers so that the higher velocity jets are projected at the higher heat load leading edge and forward convex surface areas of the vane, while the jets issuing from the lower pressure rearward chambers are projected at a lower velocity for cooling the relativeiy lower heat load regions of the airfoil vane.
  • the relatively closer spaced rows of ports throughout the midchord region is to obtain more uniform cooling than would be obtained with widely-spaced high velocity jets.
  • Typical pressures at which the chambers can be maintained may be in order of, for example, 160 psig (1102 E+03Pa) for the forward chamber, 155 psig (1068 E+03Pa) for the rearward chambers, with the pressures in the spaces between the insert and the opposing vane walls being 150 psig (1033 E+03Pa).

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

Claims (6)

1. Eine Verbrennungsturbine mit tragflügelförmigen, hohlen Turbinenleitschäufeln (12), die Vorderkantenwände, Hinterkantenteile (18) mit darin befindlichen Luftaustrittsschlitzen (20) und Seitenwände (14, 16) an den Druck- und Saugseiten aufweisen, die innere, in Verbindung mit den Luftaustrittsschlitzen stehende Hohlräume definieren, mit hohlen Einsatzteilen (22), deren Querschnitt im wesentlichen eine komplementäre Tragflächenform aufweist, die in den Hohlräumen liegen und sich in Sehnenrichtung im wesentlichen über die ganze Ausdehnung der Hohlräume erstrecken und einen Abstand von deren Wänden aufweisen, dadurch gekennzeichnet, daß die Einsatzteile (22) einzelne, einstückige Strukturen mit einer Vielzahl von sich in radialer Richtung erstreckenden Unterteilungen (38, 40, 42) in jedem Einsatzstück sind, die deren Inneres in eine Vorderkammer (30) im Bereich der Vorderkante der Leitschaufel (12) und in mindestens zwei getrennte, aufeinanderfolgende Hinterkammern (32, 34, 36) aufteilen, die miteinender in Verbindung stehen, eine Vielzahl von Auftrefföffnungen (56, 58, 60) in den Wänden der Einsatzstücke aller Kammern (30-36), wobei ein radialer Endteil der Kammern in Verbindung mit einer Kühlluftquelle steht, und daß Vorrichtungen (52, 54) vorgesehen sind, um die Strömung in die Hinterkammern (32-36) zu drosseln, so daß die Vorderkammer (30) einen relativ höheren Druck aufweist als die Hinterkammern (32, 34, 36) und die Auftreffstahlstömungen durch die Öffnungen (56) der Vorderkammer (30) gegen die Innenwände (14, 16) der Leitschaufel im Teil der Vorderkante eine wesentlich höhere Geschwindigkeit aufweisen als die Auftreffstrahlströme, die von den Öffnungen (58, 60) der Hinterkammern (32, 34, 36) ausgehen.
2. Eine Turbine nach Anspruch 1, dadurch gekennzeichnet, daß die Auftrefföffnungen (56) in der Vorderkammer (30) in einem größeren Abstand voneinander angeordnet sind als die Auftrefföffnungen (58, 60) in den Hinterkammern (32, 34, 36).
3. Eine Turbine nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Drosselvorrichtungen einen radial nach außen weisenden Teil (48) des Einsatzstückes (22) an den radial außen liegenden Enden der Hinterkammern (32, 34, 36) enthält und eine Vielzahl von Drossellöchern (54) im genannten Teil (48) des Einsatzstücks (22).
4. Eine Turbine nach irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß die Hinterkammern mindestens drei Kammern umfassen.
5. Ein Turbine nach irgendeinem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß die unterteilungen (38, 40, 42) starr verlaufende Rippen umfassen, wobei die erste Rippe (38), die die Vorderkammer (30) von der ersten der aufeinanderfolgenden Hinterkammern (32) trennt, nicht durchlöchert ist und aufeinanderfolgend weiter hinten liegende Rippen (40, 42) Öffnungen (62) aufweisen.
6. Eine Verbrennungsturbine nach Anspruch 5, dadurch gekennzeichnet, daß die zweiten Rippen (40, 42) sich weniger weit radial nach außen erstrecken als die erste Rippe (38), so daß die Hinterkammern (32, 34, 36) in ihren radial außen liegenden Teilen in offener Verbindung miteinander stehen.
EP85308230A 1984-11-15 1985-11-13 Mehrkammereinsatz zur Kühlung einer Turbinenschaufel Expired EP0182588B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US67184684A 1984-11-15 1984-11-15
US671846 1984-11-15

Publications (2)

Publication Number Publication Date
EP0182588A1 EP0182588A1 (de) 1986-05-28
EP0182588B1 true EP0182588B1 (de) 1988-09-28

Family

ID=24696102

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85308230A Expired EP0182588B1 (de) 1984-11-15 1985-11-13 Mehrkammereinsatz zur Kühlung einer Turbinenschaufel

Country Status (9)

Country Link
EP (1) EP0182588B1 (de)
JP (1) JPS61126302A (de)
KR (1) KR860004224A (de)
CN (1) CN1004291B (de)
CA (1) CA1221915A (de)
DE (1) DE3565298D1 (de)
IN (1) IN163070B (de)
IT (1) IT1186049B (de)
MX (1) MX161444A (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9850763B2 (en) 2015-07-29 2017-12-26 General Electric Company Article, airfoil component and method for forming article
US10260363B2 (en) 2016-12-08 2019-04-16 General Electric Company Additive manufactured seal for insert compartmentalization
US10655477B2 (en) 2016-07-26 2020-05-19 General Electric Company Turbine components and method for forming turbine components
US10697309B2 (en) 2018-04-25 2020-06-30 Raytheon Technologies Corporation Platform cover plates for gas turbine engine components

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GB2189553B (en) * 1986-04-25 1990-05-23 Rolls Royce Cooled vane
US5212940A (en) * 1991-04-16 1993-05-25 General Electric Company Tip clearance control apparatus and method
US5207556A (en) * 1992-04-27 1993-05-04 General Electric Company Airfoil having multi-passage baffle
US6183192B1 (en) * 1999-03-22 2001-02-06 General Electric Company Durable turbine nozzle
DE10004128B4 (de) 2000-01-31 2007-06-28 Alstom Technology Ltd. Luftgekühlte Turbinenschaufel
US6609880B2 (en) * 2001-11-15 2003-08-26 General Electric Company Methods and apparatus for cooling gas turbine nozzles
US6652220B2 (en) * 2001-11-15 2003-11-25 General Electric Company Methods and apparatus for cooling gas turbine nozzles
US7008185B2 (en) * 2003-02-27 2006-03-07 General Electric Company Gas turbine engine turbine nozzle bifurcated impingement baffle
US7871246B2 (en) * 2007-02-15 2011-01-18 Siemens Energy, Inc. Airfoil for a gas turbine
CN104088673B (zh) * 2008-11-07 2016-03-09 三菱日立电力系统株式会社 涡轮用叶片
CN101825115B (zh) * 2010-03-31 2011-09-28 北京航空航天大学 一种内置排骨架式气动阻尼的叶片
US20130104567A1 (en) * 2011-10-31 2013-05-02 Douglas Gerard Konitzer Method and apparatus for cooling gas turbine rotor blades
US9004866B2 (en) * 2011-12-06 2015-04-14 Siemens Aktiengesellschaft Turbine blade incorporating trailing edge cooling design
US9506351B2 (en) 2012-04-27 2016-11-29 General Electric Company Durable turbine vane
EP2706195A1 (de) * 2012-09-05 2014-03-12 Siemens Aktiengesellschaft Kühleinsatz mit einer Trennwand zur Prallkühlung einer Leitschaufel
WO2016036366A1 (en) 2014-09-04 2016-03-10 Siemens Aktiengesellschaft Internal cooling system with insert forming nearwall cooling channels in an aft cooling cavity of a gas turbine airfoil
GB201417476D0 (en) 2014-10-03 2014-11-19 Rolls Royce Plc Internal cooling of engine components
US10329932B2 (en) 2015-03-02 2019-06-25 United Technologies Corporation Baffle inserts
US9849510B2 (en) 2015-04-16 2017-12-26 General Electric Company Article and method of forming an article
US9976441B2 (en) 2015-05-29 2018-05-22 General Electric Company Article, component, and method of forming an article
US10253986B2 (en) 2015-09-08 2019-04-09 General Electric Company Article and method of forming an article
US10087776B2 (en) 2015-09-08 2018-10-02 General Electric Company Article and method of forming an article
US10739087B2 (en) * 2015-09-08 2020-08-11 General Electric Company Article, component, and method of forming an article
US10400608B2 (en) * 2016-11-23 2019-09-03 General Electric Company Cooling structure for a turbine component
US10494948B2 (en) * 2017-05-09 2019-12-03 General Electric Company Impingement insert
US10480347B2 (en) 2018-01-18 2019-11-19 United Technologies Corporation Divided baffle for components of gas turbine engines

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US2873944A (en) * 1952-09-10 1959-02-17 Gen Motors Corp Turbine blade cooling
FR1177035A (fr) * 1957-05-28 1959-04-20 Snecma Procédé et dispositif de refroidissement d'organes de machines
US3540810A (en) * 1966-03-17 1970-11-17 Gen Electric Slanted partition for hollow airfoil vane insert
US3891348A (en) * 1972-04-24 1975-06-24 Gen Electric Turbine blade with increased film cooling
GB1587401A (en) * 1973-11-15 1981-04-01 Rolls Royce Hollow cooled vane for a gas turbine engine
CH584346A5 (de) * 1974-11-08 1977-01-31 Bbc Sulzer Turbomaschinen
US4297077A (en) * 1979-07-09 1981-10-27 Westinghouse Electric Corp. Cooled turbine vane

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9850763B2 (en) 2015-07-29 2017-12-26 General Electric Company Article, airfoil component and method for forming article
US10655477B2 (en) 2016-07-26 2020-05-19 General Electric Company Turbine components and method for forming turbine components
US10260363B2 (en) 2016-12-08 2019-04-16 General Electric Company Additive manufactured seal for insert compartmentalization
US10697309B2 (en) 2018-04-25 2020-06-30 Raytheon Technologies Corporation Platform cover plates for gas turbine engine components

Also Published As

Publication number Publication date
IT8522785A0 (it) 1985-11-11
MX161444A (es) 1990-09-27
JPH0379522B2 (de) 1991-12-19
CN1004291B (zh) 1989-05-24
JPS61126302A (ja) 1986-06-13
IN163070B (de) 1988-08-06
IT1186049B (it) 1987-11-18
DE3565298D1 (en) 1988-11-03
CA1221915A (en) 1987-05-19
CN85108282A (zh) 1986-08-27
KR860004224A (ko) 1986-06-18
EP0182588A1 (de) 1986-05-28

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