EP1892383A1 - Ailette de turbine à gaz à plate-forme refroidie - Google Patents

Ailette de turbine à gaz à plate-forme refroidie Download PDF

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Publication number
EP1892383A1
EP1892383A1 EP06017639A EP06017639A EP1892383A1 EP 1892383 A1 EP1892383 A1 EP 1892383A1 EP 06017639 A EP06017639 A EP 06017639A EP 06017639 A EP06017639 A EP 06017639A EP 1892383 A1 EP1892383 A1 EP 1892383A1
Authority
EP
European Patent Office
Prior art keywords
platform
edge
turbine blade
slot
cooling
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.)
Withdrawn
Application number
EP06017639A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Michael Dr. Dankert
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 EP06017639A priority Critical patent/EP1892383A1/fr
Priority to PCT/EP2007/056422 priority patent/WO2008022830A1/fr
Publication of EP1892383A1 publication Critical patent/EP1892383A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • the invention relates to a turbine blade for a particularly stationary gas turbine, having a mounting area adjoined by a platform and an airfoil profile thereon, with a surface that can be acted upon by a hot gas and is delimited by a peripheral platform edge with an end-side edge surface. wherein at least one recess which extends in the direction of the platform edge is provided in the edge surface.
  • Such turbine blades are used in stationary gas turbines. So that they withstand the hot temperatures of the working medium of the gas turbine, the turbine blades are cooled. In addition, penetration of hot working medium into the gap formed by two platforms of adjacent turbine blades is avoided by blowing out cooling air therefrom.
  • the cooling air can be supplied. Due to the prevailing pressure conditions in the turbine, the cooling air exits from this groove and thus prevents the harmful penetration of hot gas into the gap.
  • the cooling air flowing out of the groove cools the edge of the platform beyond the required requirement.
  • the material temperature near the edge of the platform is thus substantially lower than in the areas of the surface of the platform which are remote from the edge of the platform.
  • the occurring temperature gradients and the temperature-dependent material expansions can possibly lead to wear at this point, which occurs in the form of cracking and crack growth.
  • the surface of the platform has a coating to protect against corrosion and heat input has that due to the large material expansions of the platform this coating peels off locally, whereby the protective effect is lost at the affected sites.
  • the object of the invention is therefore to provide a generic turbine blade for a particular stationary gas turbine, which has a particularly long life.
  • a generic turbine blade which has the features of claim 1. It is proposed that at least one of the recesses is designed as a slot which extends into the platform and that the or each slot for cooling the surface of the platform can be flowed through by a coolant in the direction of the platform edge.
  • the material temperature of the platform is lowered in the region remote from the platform edge due to the cooling provided there, compared with a turbine blade known from the prior art.
  • the cooling air absorbs so much heat energy that its cooling effect at the edge of the platform, at which the cooling air leaves the turbine blade, is less intense compared to the turbine blade known from the prior art. Accordingly, the platform edge is no longer needed, but cooled as needed.
  • the material temperature of the platform, near the edge of the platform is no longer unduly lowered.
  • the temperature difference in the platform material between the platform edge and the area remote from the platform edge is adjusted, so that lower material stresses and temperature-related strains occur. Wear in the form of cracks thus occurs less often, or if cracks already exist, their growth will take place more slowly than in a known turbine blade.
  • the turbine blade according to the invention has a prolonged service life compared with the known turbine blade.
  • a sufficient amount of cooling air can be provided for blocking the gap without pressure loss, if in the turbine blade a plurality of slots stacked inside the platform are provided, whose slot openings open in the edge surface of the platform edge. Expediently, the slots have different slot depths, as seen from the edge surface.
  • the or each slot each having a slot opening opposite slot bottom, wherein the supply of coolant in the region of the slot bottom occurs.
  • the planar platform cooling can be done comparatively easily in a convective manner.
  • the temperatures in the area remote from the platform edge are thereby lowered, which leads to a further homogenization of the platform temperatures.
  • the turbine blade when the turbine blade is designed as a blade for a turbine, a particularly long-lived turbine blade can be specified, since usually arranged in the region of the platform edge damper wires represent a further mechanical stress, which, however, does not reduce life due to the inventive design of the turbine blade.
  • a turbine blade 10 is shown in a perspective view.
  • the cast blade has a designated as a blade root attachment region 12, at which a platform 14 and a wing profile 16 adjoins it.
  • a hot working medium flows around the airfoil profile 16 and is also guided by the surface 18 of the platform 14 within an annular, not shown, flow channel.
  • the surface 18 of the platform 14 is bounded by a peripheral platform edge 20.
  • the peripheral platform edge 20 is divided into two mutually parallel longitudinal edges 24 and two transversely extending transverse edges 26.
  • each formed as slots 28 are provided whose slot depth is selected such that they protrude comparatively deep into the platform 14, far away from the platform edge 20.
  • Each slot 28 has a slot opening 32 located in the edge surface 22, the slot base 34 opposite the slot opening 32 being located so deep within the platform 14 that it terminates near the airfoil 16 or even partially below it, as seen radially.
  • a coolant which can flow on the underside of the platform 38 can be supplied to the slot 28, as seen in the radial direction of the turbine blade 10. In this case, the surface 18 exposed to the hot gas of the platform 14 is crust-cooled in places.
  • the coolant flows due to the prevailing pressure gradient to the slot opening 28 and cools the platform 14 convectively.
  • the meanwhile warming coolant locks after the outflow from the slot openings 28 enclosed by two edge surfaces 22 of adjacent turbine blades 10 gap against hot gas intake. Since the coolant has already absorbed heat energy due to the impingement cooling and the subsequent convective planar cooling of the platform 14 toward the slot opening 32, the platform edge 20 of the platform longitudinal edge 24 is cooled less, but still sufficiently cooled, compared to a turbine blade known from the prior art ,
  • the temperatures which are set from the blade center in the direction of the platform edge 20 are thus adjusted in a particularly efficient manner. As a result, less temperature-induced stresses arise in the platform 14, so that cracking is delayed and crack growth slows down compared to a turbine blade known from the prior art.
  • FIG. 3 shows the section through the longitudinal section of the turbine blade according to the invention according to FIG. 1, identical features being provided with the same reference numerals.
  • FIG. 4 shows an alternative embodiment of a turbine blade platform 14 according to the invention, in which a meandering slot 28 is cast. Again, the supply of coolant from the platform base 38, wherein the slot 28 extends in the illustrated example partially below the airfoil 16.
  • the invention provides a turbine blade 10, the life of which is compensated by equalizing the temperatures in the platform 14 in the direction of the airfoil 16 towards the platform edge 20 due to an increase in the cooling air temperature at the slot opening 28 relative to a known turbine blade is. An inadmissibly strong cooling of the platform edge 20 is thus avoided.
  • the life, in particular LCF life (low cycle fatigue life) of the turbine blade 10 according to the invention can be further increased.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06017639A 2006-08-24 2006-08-24 Ailette de turbine à gaz à plate-forme refroidie Withdrawn EP1892383A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP06017639A EP1892383A1 (fr) 2006-08-24 2006-08-24 Ailette de turbine à gaz à plate-forme refroidie
PCT/EP2007/056422 WO2008022830A1 (fr) 2006-08-24 2007-06-27 aube de turbine à gaz à plate-forme refroidie

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06017639A EP1892383A1 (fr) 2006-08-24 2006-08-24 Ailette de turbine à gaz à plate-forme refroidie

Publications (1)

Publication Number Publication Date
EP1892383A1 true EP1892383A1 (fr) 2008-02-27

Family

ID=37685118

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06017639A Withdrawn EP1892383A1 (fr) 2006-08-24 2006-08-24 Ailette de turbine à gaz à plate-forme refroidie

Country Status (2)

Country Link
EP (1) EP1892383A1 (fr)
WO (1) WO2008022830A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2264283A3 (fr) * 2009-06-15 2015-06-03 Rolls-Royce plc Composant refroidi pour moteur à turbine à gaz
EP2885520A4 (fr) * 2012-08-14 2015-08-12 United Technologies Corp Composant de moteur à turbine à gaz ayant une tranchée de plateforme

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2915279A (en) * 1953-07-06 1959-12-01 Napier & Son Ltd Cooling of turbine blades
US3182955A (en) * 1960-10-29 1965-05-11 Ruston & Hornsby Ltd Construction of turbomachinery blade elements
GB2169356A (en) * 1984-12-17 1986-07-09 United Technologies Corp Coolable stator assembly for a gas turbine engine
EP0357984A1 (fr) * 1988-08-31 1990-03-14 Westinghouse Electric Corporation Turbine à gaz à refroidissement pelliculaire de frettes de distributeur
US5639216A (en) * 1994-08-24 1997-06-17 Westinghouse Electric Corporation Gas turbine blade with cooled platform
EP1008723A1 (fr) * 1998-12-10 2000-06-14 ABB Alstom Power (Schweiz) AG Refroidissement de plateformes de turbomachines

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2915279A (en) * 1953-07-06 1959-12-01 Napier & Son Ltd Cooling of turbine blades
US3182955A (en) * 1960-10-29 1965-05-11 Ruston & Hornsby Ltd Construction of turbomachinery blade elements
GB2169356A (en) * 1984-12-17 1986-07-09 United Technologies Corp Coolable stator assembly for a gas turbine engine
EP0357984A1 (fr) * 1988-08-31 1990-03-14 Westinghouse Electric Corporation Turbine à gaz à refroidissement pelliculaire de frettes de distributeur
US5639216A (en) * 1994-08-24 1997-06-17 Westinghouse Electric Corporation Gas turbine blade with cooled platform
EP1008723A1 (fr) * 1998-12-10 2000-06-14 ABB Alstom Power (Schweiz) AG Refroidissement de plateformes de turbomachines

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2264283A3 (fr) * 2009-06-15 2015-06-03 Rolls-Royce plc Composant refroidi pour moteur à turbine à gaz
EP2885520A4 (fr) * 2012-08-14 2015-08-12 United Technologies Corp Composant de moteur à turbine à gaz ayant une tranchée de plateforme
US10364680B2 (en) 2012-08-14 2019-07-30 United Technologies Corporation Gas turbine engine component having platform trench

Also Published As

Publication number Publication date
WO2008022830A1 (fr) 2008-02-28

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