EP1309773A1 - Dispositif d'aubes directrices de turbine - Google Patents

Dispositif d'aubes directrices de turbine

Info

Publication number
EP1309773A1
EP1309773A1 EP01962905A EP01962905A EP1309773A1 EP 1309773 A1 EP1309773 A1 EP 1309773A1 EP 01962905 A EP01962905 A EP 01962905A EP 01962905 A EP01962905 A EP 01962905A EP 1309773 A1 EP1309773 A1 EP 1309773A1
Authority
EP
European Patent Office
Prior art keywords
cooling air
guide vane
turbine guide
duct
channel
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
EP01962905A
Other languages
German (de)
English (en)
Other versions
EP1309773B1 (fr
Inventor
Hans-Thomas Bolms
Michael Strassberger
Peter Tiemann
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 EP01962905A priority Critical patent/EP1309773B1/fr
Publication of EP1309773A1 publication Critical patent/EP1309773A1/fr
Application granted granted Critical
Publication of EP1309773B1 publication Critical patent/EP1309773B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • 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
    • 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

Definitions

  • the invention relates to an arrangement of turbine guide vanes, in particular turbine guide vanes of the rearmost stages, each having a radially outer foot region, a radially inner head region and a radial cooling air duct running between the head region and foot region, can be introduced into the cooling air into an inlet opening in the foot region and through an outlet opening in the head area can be at least partially led out.
  • a hot gas stream driving a turbine is conducted from the stationary turbine guide vanes to the turbine rotor blades, which are fastened on disks rotating about a central turbine axis.
  • the radially inner head regions of the turbine guide vanes adjoin a U-shaped inner ring which has a labyrinth seal on its outside, which seals against the flow of hot gas around the U-ring.
  • Cooling air is generally used to cool the turbine blades heated by the hot gas flowing past.
  • the cooling air flows, for example, through a radial cooling air duct arranged in the turbine guide vane, from the radially outer root region of the turbine guide vane to the radially inner head region / the cooling air is introduced from the head region into the adjacent U-shaped ring. This is cooled by the cooling air flowing past.
  • An overpressure of the cooling air is also intended to prevent hot gas from entering the area of the head c ⁇ K 1V> F 1 F »
  • F- O o_ 3 N - O: P- rt F- ⁇ 0 ⁇ tr F- t tr ⁇ J ⁇ F ⁇ . ⁇ P.
  • the division of the cooling air duct into the inner and outer duct ensures that the cooling air first flows through the inner duct, and flows out at the foot region partly for cooling the U-shaped ring and partly flows back again after being diverted through the outer duct.
  • the total amount of cooling air flows through the inner duct and a smaller amount of cooling air flows around it in the form of a counterflow.
  • the cooling air flow in the outer duct surrounding the inner duct is very fast. It therefore provides good cooling of the surrounding areas of the turbine guide vane due to the increased cooling capacity of a fast cooling air flow.
  • the cooling air flowing back in a rapid flow isolates the inner channel on the one hand and enables the cooling air at the outflow point into the U-ring at the head region to have a low temperature without large amounts of cooling air having to be used.
  • the cooling air flowing back cools the side walls of the cooling air duct and thus the surrounding areas of the turbine guide vane, which are the load-bearing areas of the turbine guide vane.
  • the walls of the turbine blade, which surround the cooling air duct are thicker than in the prior art and thus more stable.
  • the invention thus offers the advantage that both the turbine guide vane and the U-shaped ring are sufficiently cooled with small amounts of cooling air.
  • turbine guide vanes are turbine guide vanes of the rearmost stages, there is a relatively large saving compared to the use of conventional cooling air ducts 00 c ⁇ tt F 1 F 1
  • F cn p F tr 0 0 0 0 0 0 rt EP M o tr ⁇ F "P P- F- rt C ⁇ ⁇ rt F- 0 ü rt 0 PF EP 0 0 P ⁇ N F- cn F 1 ⁇ 0 F- F 1 ⁇ ⁇ ⁇ F- ⁇ 0 ⁇ ⁇ F- ⁇ rt Hi
  • F 0 0 p: O - Hi tr ⁇ 3 ⁇ ⁇ ⁇ 0 ⁇ F- ⁇ ⁇ P- 0 ⁇ rt 3 0 vq ⁇ F "F ⁇ F-
  • the cooling of the turbine guide vane is sufficient at the relatively low temperatures, especially in the rear stages.
  • Fig. 2 shows a longitudinal section through a turbine guide vane according to Fig.l and
  • FIG. 3 shows a schematic representation of the temperature development of the cooling air mass flows.
  • Fig. 1 shows a perspective view of a turbine guide vane 1 of the rearmost stages.
  • the turbine guide vane 1 With the help of the foot region 2, which has holding projections 24, the turbine guide vane 1 is fastened to an inner wall, not shown, of a cylindrical turbine housing. From there, the turbine guide vane 1 extends with its blade 18 radially in the direction of a central turbine axis 30 of the turbine housing.
  • the radially inner end of the turbine guide vane 1 is formed by the head region 3, which has a plateau 25 and an arcuate recess 26 which is radially inner with respect to the turbine axis 30.
  • a U-shaped ring 19 is coupled to this head region 3 by means of rail-like holding projections 27. The holding projections 27 engage in holding grooves 28 of the U-shaped ring 19.
  • a labyrinth seal 21 is located radially on the inside of the U-shaped ring 19. This seals the turbine rotor blade disk 22, which is located underneath and rotates around the central turbine axis 31 when the turbine is in operation Turbine blades, not shown, is occupied, against a direct flow of hot gas 17.
  • the airfoil 18 has a radial, cylindrical cooling air channel 4 which runs continuously from an inlet opening 36 of the cooling air 23 in the foot region 2 of the turbine guide vane 1 to its outlet opening 35 of the cooling air in the head region 3 of the turbine guide vane 1. It has a cross-sectional contour 34 which in the area of the airfoil 18 and the foot area 2 is similar to the outer contour 16 of the airfoil 18. When viewed from the foot area 2 to in front of the head area 3, the shape of the cross-sectional contour 34 of the cooling air duct 4 remains essentially the same, but may decrease in size. When the cooling air duct 4 enters the head region 3, the cross section 34 in narrows
  • the cooling air guide tube 13 is held in the center, for example, by spacing webs 37 attached to side walls 8 of the cooling air duct 4.
  • the cooling air duct 4 can be cast directly during the casting of the turbine blade 1 by inserting a casting core.
  • the cooling air guide tube 13 is inserted into the cooling air duct 4 after the casting.
  • the cooling air 23 is introduced into the inlet opening 36 of the cooling air guide tube 13, which extends to an upper side 32 of the foot area 2 of the turbine guide vane 1.
  • the maximum temperature Tmax is not reached by the continuous current 42, as a result of which the U-shaped ring can be cooled sufficiently.
  • the other cooling air portion 41 takes the greater part of the heat and transports it out of the turbine blade without the heat being able to damage the temperature-sensitive areas.
  • the total amount of cooling air 23, the sum of the two power components 41, 42 is significantly lower than in the prior art.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
  • Ink Jet Recording Methods And Recording Media Thereof (AREA)

Abstract

L'invention concerne une aube directrice de turbine (1), en particulier une aube directrice de turbine des derniers étages, respectivement constituée d'une zone inférieure (2) située radialement à l'extérieur, d'une zone supérieure (3) située radialement à l'intérieur, et d'un canal d'air (4) de refroidissement radial s'étendant entre la zone inférieure et la zone supérieure, de l'air de refroidissement (23) pouvant être introduit dans ledit canal par l'intermédiaire d'une ouverture d'entrée (36) située dans la zone inférieure et évacué au moins partiellement par l'intermédiaire d'une ouverture de sortie (35) située dans la zone supérieure. Ledit canal d'air de refroidissement présente un canal intérieur radial au travers duquel l'air de refroidissement s'écoule de la zone inférieure vers la zone supérieure, et un canal extérieur (9) adjacent au canal intérieur, enveloppant au moins partiellement le canal intérieur côté périphérique. Ledit canal extérieur communique avec le canal intérieur et présente une ouverture de sortie (12) située dans la zone inférieure, une partie de l'air de refroidissement (41) recirculant au travers du canal extérieur en direction de la zone inférieure et sortant par l'ouverture de sortie.
EP01962905A 2000-08-16 2001-08-03 Dispositif d'aubes directrices de turbine Expired - Lifetime EP1309773B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01962905A EP1309773B1 (fr) 2000-08-16 2001-08-03 Dispositif d'aubes directrices de turbine

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP00117667A EP1180578A1 (fr) 2000-08-16 2000-08-16 Aubes statoriques pour une turbomachine
EP00117667 2000-08-16
PCT/EP2001/009015 WO2002014654A1 (fr) 2000-08-16 2001-08-03 Dispositif d'aubes directrices de turbine
EP01962905A EP1309773B1 (fr) 2000-08-16 2001-08-03 Dispositif d'aubes directrices de turbine

Publications (2)

Publication Number Publication Date
EP1309773A1 true EP1309773A1 (fr) 2003-05-14
EP1309773B1 EP1309773B1 (fr) 2005-12-21

Family

ID=8169551

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00117667A Withdrawn EP1180578A1 (fr) 2000-08-16 2000-08-16 Aubes statoriques pour une turbomachine
EP01962905A Expired - Lifetime EP1309773B1 (fr) 2000-08-16 2001-08-03 Dispositif d'aubes directrices de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP00117667A Withdrawn EP1180578A1 (fr) 2000-08-16 2000-08-16 Aubes statoriques pour une turbomachine

Country Status (6)

Country Link
US (1) US7201564B2 (fr)
EP (2) EP1180578A1 (fr)
JP (1) JP4726389B2 (fr)
DE (1) DE50108476D1 (fr)
ES (1) ES2255567T3 (fr)
WO (1) WO2002014654A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1728973A1 (fr) 2005-06-01 2006-12-06 Siemens Aktiengesellschaft Procédé pour le blocage du jeu dans une turbomachine et turbomachine pour la réalisation du procédé
US8182205B2 (en) * 2007-02-06 2012-05-22 General Electric Company Gas turbine engine with insulated cooling circuit
US20100000219A1 (en) * 2008-07-02 2010-01-07 General Electric Company Systems and Methods for Supplying Cooling Air to a Gas Turbine
US8251652B2 (en) * 2008-09-18 2012-08-28 Siemens Energy, Inc. Gas turbine vane platform element
US8162598B2 (en) * 2008-09-25 2012-04-24 Siemens Energy, Inc. Gas turbine sealing apparatus
US8388309B2 (en) * 2008-09-25 2013-03-05 Siemens Energy, Inc. Gas turbine sealing apparatus
US8376697B2 (en) * 2008-09-25 2013-02-19 Siemens Energy, Inc. Gas turbine sealing apparatus
US8397516B2 (en) * 2009-10-01 2013-03-19 General Electric Company Apparatus and method for removing heat from a gas turbine
US20120003076A1 (en) * 2010-06-30 2012-01-05 Josef Scott Cummins Method and apparatus for assembling rotating machines
US8662826B2 (en) * 2010-12-13 2014-03-04 General Electric Company Cooling circuit for a drum rotor
US9403208B2 (en) 2010-12-30 2016-08-02 United Technologies Corporation Method and casting core for forming a landing for welding a baffle inserted in an airfoil
GB201112803D0 (en) 2011-07-26 2011-09-07 Rolls Royce Plc Master component for flow calibration
WO2014200673A1 (fr) 2013-06-14 2014-12-18 United Technologies Corporation Aube de turbine à rayon interne de bord de fuite variable
US20150013344A1 (en) * 2013-07-15 2015-01-15 United Technologies Corporation Tube
EP2840231A1 (fr) * 2013-08-23 2015-02-25 Siemens Aktiengesellschaft Aube de turbine dotée d'une pale creuse
US9435212B2 (en) * 2013-11-08 2016-09-06 Siemens Energy, Inc. Turbine airfoil with laterally extending snubber having internal cooling system
EP3149311A2 (fr) 2014-05-29 2017-04-05 General Electric Company Moteur de turbine, et épurateurs de particules pour celui-ci
US11033845B2 (en) 2014-05-29 2021-06-15 General Electric Company Turbine engine and particle separators therefore
US10125632B2 (en) 2015-10-20 2018-11-13 General Electric Company Wheel space purge flow mixing chamber
US10132195B2 (en) 2015-10-20 2018-11-20 General Electric Company Wheel space purge flow mixing chamber
US10422233B2 (en) 2015-12-07 2019-09-24 United Technologies Corporation Baffle insert for a gas turbine engine component and component with baffle insert
US10337334B2 (en) * 2015-12-07 2019-07-02 United Technologies Corporation Gas turbine engine component with a baffle insert
US10577947B2 (en) 2015-12-07 2020-03-03 United Technologies Corporation Baffle insert for a gas turbine engine component
US10280841B2 (en) 2015-12-07 2019-05-07 United Technologies Corporation Baffle insert for a gas turbine engine component and method of cooling
US10975708B2 (en) * 2019-04-23 2021-04-13 Rolls-Royce Plc Turbine section assembly with ceramic matrix composite vane
CN113236371B (zh) * 2021-06-04 2023-01-17 中国航发沈阳发动机研究所 一种叶片冷气导管

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Also Published As

Publication number Publication date
ES2255567T3 (es) 2006-07-01
US7201564B2 (en) 2007-04-10
JP4726389B2 (ja) 2011-07-20
EP1309773B1 (fr) 2005-12-21
DE50108476D1 (de) 2006-01-26
WO2002014654A1 (fr) 2002-02-21
US20030180147A1 (en) 2003-09-25
EP1180578A1 (fr) 2002-02-20
JP2004506827A (ja) 2004-03-04

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