EP1309773B1 - Dispositif d'aubes directrices de turbine - Google Patents

Dispositif d'aubes directrices de turbine Download PDF

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Publication number
EP1309773B1
EP1309773B1 EP01962905A EP01962905A EP1309773B1 EP 1309773 B1 EP1309773 B1 EP 1309773B1 EP 01962905 A EP01962905 A EP 01962905A EP 01962905 A EP01962905 A EP 01962905A EP 1309773 B1 EP1309773 B1 EP 1309773B1
Authority
EP
European Patent Office
Prior art keywords
cooling
duct
cooling air
air
turbine
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
EP01962905A
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German (de)
English (en)
Other versions
EP1309773A1 (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

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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
    • 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 vanes of the rearmost stages, each with a radially outwardly arranged foot area, a radially inwardly disposed head portion and an intermediate Head region and foot region extending radial cooling air channel, in the cooling air in an inlet opening in the foot area introducible and through an outlet opening in the head area is at least partially derivable.
  • a hot gas stream driving a turbine is driven by the stationary one Turbine vanes to the turbine blades, the disks revolving around a central turbine axis are fixed, conducted.
  • a circular arrangement of Turbine vanes, with their radially outer foot areas mounted on a stationary turbine casing wall are alternated with an arrangement of turbine blades on a spinning disc.
  • the radial inner head portions of the turbine vanes adjoin one another U-shaped inner ring, the one on its outside Labyrinth seal has, against the flow around the U-ring sealed with hot gas.
  • Turbine blades For cooling the heated by the passing hot gas Turbine blades are usually used cooling air.
  • the cooling air flows by a radial vane mounted in the turbine vane Cooling air duct from the radially outer foot region of the turbine guide vane to the radially inner head area. From the head area the cooling air is in the adjacent U-shaped ring initiated. This is due to the passing cooling air cooled.
  • an overpressure of the cooling air should also be prevented be that hot gas in the from the head area of the Turbine vanes and the underlying U-shaped Ring formed cavity penetrates.
  • the problem is that the U-shaped ring of manufacturing and cost reasons mostly from a little temperature resistant Material exists.
  • the cooling air usually heats up to the maximum permissible temperature of the turbine vane.
  • the cooling air thus already has when flowing into the U-ring a fairly high temperature and may be at the low Cooling air quantities required for cooling the turbine vane a rear stage compared to the other turbine vane stages not very warm, would suffice, do not provide sufficient cooling of the U-ring.
  • This is also problematic because of the U-ring and the cavity formed in the turbine bucket head area Cooling air discharged after flowing through the cavity and towards the farthest, largely uncooled, heat-sensitive turbine blade disk flows.
  • the previous problem solution consists in a lot of cooling air through a central bore of a turbine vane or through a cooling air duct of a largely hollow cast To guide turbine vane.
  • Object of the present invention is therefore an arrangement Turbine vanes create a lower Has cooling air demand, wherein at the same time the U-shaped Ring is sufficiently cooled.
  • the inner channel in a thede povertykanal usablemé Kunststoffleitrohr is, with arranged a distance from inner walls of the cooling air duct and the outer channel through the gap betweende povertyleitrohr and the inner walls of the cooling air channel is formed, wherein the distance is less than a cross section of thedeluftleitrohres.
  • the production of the cooling channel is simplified.
  • Thede povertyleitrohr can after casting in the Cooling air duct can be used.
  • the outer channel then exists from the space extending around the cooling air duct.
  • the thickness of the gap which is the distance of thede Kunststoffleitrohrs from the side walls of the cooling air duct can be adjusted as needed. The narrower the gap is, the faster the speed the squeezed through cooling air. By an increasing cooling air speed in turn increases its ability to dissipate heat.
  • the cooling air duct By dividing the cooling air duct into the inner and outer channels is achieved that the cooling air first through the inner channel flows and at the foot area partly for cooling the U-shaped Flows out and partly again after diverting flows back through the outer channel.
  • the inner channel becomes flowed through by the total amount of cooling air and a smaller Cooling air flow in the form of a counterflow.
  • the Cooling air flow in the outer channel surrounding the outer channel is included very fast. Thus, it provides a good cooling of the surrounding Areas of the turbine vane due to the increased Cooling performance of a fast cooling air flow.
  • the cooling air flowing back cools the side walls of the cooling air duct and thus the surrounding Areas of the turbine vane that the load-bearing Are areas of the turbine vane.
  • the walls of the Turbine blades surrounding the cooling air duct are in accordance with the invention thicker than in the prior art and thus more stable.
  • the invention thus offers the advantage that with low amounts of cooling air both the turbine vane as well as the U-shaped ring sufficiently cooled become.
  • the heat radiation through the inner channel directed cooling air almost all sides of the part the cooling air, which can be conducted through the outer channel, dissipated. Due to the large radiation area is a big one Heat transfer possible in a short time.
  • the arriving in the head area Cooling air thus has a very low temperature and can cool the U-shaped ring optimally.
  • the inner channel has at least one communication bore, can pass through the cooling air into the outer channel, the cooling air is accelerated very strong at the bore point. This improves the cooling properties of the cooling air in the Outdoor channel, because of the higher speed more heat can be included.
  • a long cooling air path inside the turbine vane and thus a good utilization of the cooling air is achieved if the inner channel at least at a head end portion has a communication hole.
  • the cooling air can the cooling air tube over almost the entire length between head and shield foot area from the hot paddle wall, so that emerging in the head region of the turbine vane Cooling air even with a small flow of cooling air in the inner channel has a sufficiently low temperature to the U-shaped Ring to cool well.
  • the cooling air flow flowing back in the outer channel At the same time it cools the surrounding areas of the turbine vane.
  • the turbine guide vane at the foot has an outlet opening in a trailing edge region, which communicates with the outer channel.
  • the Outlet opening occurs diverted cooling air, which on the inner channel past the turbine vane, without mixing with the introduced cooling air gives.
  • the arrangement of the outlet opening in the trailing edge region prevents ingress of inflowing hot gas, the would lead to damage.
  • the cooling air takes a very long distance inside the turbine vane and can also work with smaller amounts of cooling air absorb a lot of heat energy from the turbine vane and dissipate to the outside, without the air in the inner channel would be heated.
  • the speed is and the type of flow of the circulating cooling air on the total channel length approximately the same size and thus the Heat dissipation. This is a uniform cooling performance guaranteed.
  • the task also relates to a method for Production of a turbine guide vane.
  • the object is achieved by a casting method for the production an arrangement of turbine vanes in which a Core is used, which is the cooling air duct of the turbine vane produced, wherein after casting in the cooling air duct a provided with at least one communication borede Kunststoffleitrohr with distance to the inner walls of Cooling air duct is used, and in the wall in the trailing edge area the root area of the turbine vane up to the outer contour of the turbine vane passing Outlet openings are introduced.
  • Fig. 1 shows a perspective view of a turbine vane 1 of the rearmost steps.
  • foot area 2 which has retaining projections 24, becomes the turbine vane 1 on an inner wall, not shown attached cylindrical turbine housing.
  • the turbine vane 1 With the help of the foot area 2, which has retaining projections 24, becomes the turbine vane 1 on an inner wall, not shown attached cylindrical turbine housing. From there extends the turbine vane 1 with its blade 18 radially in the direction of a central turbine axis 30th of the turbine housing.
  • the radially inner end of the turbine vane 1 forms the head area 3, which is a plateau 25 and one with respect to the turbine axis 30 radially inner arcuate recess 26 has.
  • head area 3 is by means of rail-like retaining projections 27 is a U-shaped Ring 19 docked.
  • the retaining projections 27 engage in it Retaining 28 of the U-shaped ring 19 a.
  • the airfoil 18 has a radial, cylindrical Cooling air duct 4, the continuous 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 Head portion 3 of the turbine vane 1 extends. He has a cross-sectional contour 34, which in the region of the airfoil 18 and the foot portion 2 of the outer contour 16 of the airfoil 18 is similar.
  • the cross-sectional contour 34 of the cooling air channel 4 remains in viewing from footer 2 to before Head area 3 in shape substantially preserved, can however, decrease in size.
  • the cross section 34 narrows in Shape of a circumferential step 33.
  • cooling air duct 4 mounted spacer webs 37 held centrally.
  • the cooling air duct 4 can be used during casting of the turbine blade 1 cast directly by inserting a G tellkerns become.
  • Thede povertyleitrohr 13 is after casting in the Cooling air duct 4 used.
  • FIG. 2 shows a longitudinal section through the turbine guide vane 1 according to Fig.1.
  • the entire cooling air flow 23 the foot-side End 5 flows into thede povertyleitrohr 13 is split into two cooling air flow components, the deflected Cooling air flow 41 through the holes 10 at the top End region 6 flows into the outer channel 9 and at the outlet opening 12 flows out again, and the U-shaped ring 19 outflowing cooling air flow 42.
  • FIG 3 shows the evolution of the temperature T of the cooling air flow components 41, 42, while the turbine vane 1 in the longitudinal direction 31 up to an end length 1 of the cooling air channel 4 flow through.
  • the maximum temperature Tmax is from the continuous current 42 is not reached, causing the U-shaped Ring can be sufficiently cooled.
  • the other part of cooling air 41 absorbs the greater part of the heat and carries him out of the turbine blade without the heat can damage the temperature-sensitive areas.
  • the whole Cooling air quantity 23, the sum of the two current components 41, 42 is much lower than in the prior art.

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  • 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.

Claims (8)

  1. Aube (1) directrice de turbine, notamment aube (1) directrice de turbine des étages les plus en aval, comprenant respectivement une partie (2) d'emplanture disposée à l'extérieur radialement, une partie (3) de tête disposée à l'intérieur radialement et un canal (4) radial pour de l'air de refroidissement s'étendant entre la partie (3) de tête et la partie (2) d'emplanture, et dans lequel de l'air (23) de refroidissement peut être envoyé dans une ouverture (36) d'entrée de la partie (2) d'emplanture et sortir au moins en partie par une ouverture (35) de sortie de la partie (3) de tête, le canal (4) pour de l'air de refroidissement ayant un canal intérieur radial par lequel l'air (23) de refroidissement va de la partie (2) d'emplanture à la partie (3) de tête et un canal (9) extérieur voisin du canal intérieur qui entoure au moins en partie du côté du pourtour le canal intérieur, qui communique avec le canal intérieur et qui a une ouverture (12) de sortie dans la partie (2) d'emplanture, une partie (41) de l'air de refroidissement retournant par le canal (9) extérieur en direction de la partie (2) d'emplanture et sortant par l'ouverture (12) de sortie,
       dans laquelle le canal intérieur est un tuyau (13) de canalisation de l'air de refroidissement pouvant être inséré dans le canal (4) pour de l'air de refroidissement et disposé à distance (14) de la paroi (8) intérieure du canal (4) pour de l'air de refroidissement, et le canal (9) extérieur est formé par l'espace intermédiaire compris entre le tuyau (13) de canalisation de l'air de refroidissement et la paroi (8) intérieure du canal (4) pour de l'air de refroidissement,
       caractérisée    en ce que la distance (14) est plus petite qu'une section (15) transversale du tuyau (13) de canalisation de l'air de refroidissement.
  2. Aube directrice de turbine suivant la revendication 1,
       caractérisée en ce que le canal (9) extérieur entoure le canal intérieur pratiquement complètement du côté du pourtour.
  3. Aube directrice de turbine suivant la revendication 1 ou 2,
       caractérisée en ce que le canal intérieur a au moins un trou (10) de mise en communication par lequel la partie (41) d'air de refroidissement peut passer dans le canal (9) extérieur.
  4. Aube directrice de turbine suivant la revendication 3,
       caractérisée en ce que le trou (10) de mise en communication est disposé dans une partie (6) d'extrémité du côté de la tête.
  5. Aube directrice de turbine suivant l'une des revendications 1 à 4, caractérisée en ce que l'aube (1) directrice de turbine a, dans la partie (2) d'emplanture, dans une partie (11) de bord arrière, une ouverture (12) de sortie qui communique avec le canal (9) de sortie.
  6. Aube directrice de turbine suivant l'une des revendications 1 à 5, caractérisée en ce que le canal intérieur est cylindrique.
  7. Aube directrice de turbine suivant l'une des revendications 1 à 6, caractérisée en ce que le courant de la partie (41) d'air de refroidissement dans le canal (9) extérieur est plus rapide que dans le canal (1) intérieur.
  8. Procédé de coulée pour la fabrication d'une aube directrice de turbine suivant l'une des revendications 1 à 8, dans lequel le canal (4) pour de l'air de refroidissement de l'aube (1) directrice de la turbine est produit par un noyau,
       caractérisé en ce qu'après la coulée, on utilise, dans le canal (4) pour de l'air de refroidissement, un tuyau (13) de canalisation de l'air de refroidissement muni d'au moins un trou (11) de mise en communication et à distance des parois (8) intérieures du canal (4) pour de l'air de refroidissement, et on ménage dans les parois (8) intérieures, dans la partie (11) du bord arrière de la partie (2) d'emplanture de l'aube (1) directrice de la turbine, des ouvertures (12) de sortie traversantes allant jusqu'au contour (16) extérieur de l'aube (1) directrice de la turbine.
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 EP1309773A1 (fr) 2003-05-14
EP1309773B1 true 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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EP2840231A1 (fr) * 2013-08-23 2015-02-25 Siemens Aktiengesellschaft Aube de turbine dotée d'une pale creuse
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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
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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
DE50108476D1 (de) 2006-01-26
WO2002014654A1 (fr) 2002-02-21
EP1309773A1 (fr) 2003-05-14
US20030180147A1 (en) 2003-09-25
EP1180578A1 (fr) 2002-02-20
JP2004506827A (ja) 2004-03-04

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