EP1180578A1 - Aubes statoriques pour une turbomachine - Google Patents

Aubes statoriques pour une turbomachine Download PDF

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Publication number
EP1180578A1
EP1180578A1 EP00117667A EP00117667A EP1180578A1 EP 1180578 A1 EP1180578 A1 EP 1180578A1 EP 00117667 A EP00117667 A EP 00117667A EP 00117667 A EP00117667 A EP 00117667A EP 1180578 A1 EP1180578 A1 EP 1180578A1
Authority
EP
European Patent Office
Prior art keywords
cooling air
guide vane
duct
turbine guide
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.)
Withdrawn
Application number
EP00117667A
Other languages
German (de)
English (en)
Inventor
Hans-Dieter Dr. Bolms
Michael Dr. 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 EP00117667A priority Critical patent/EP1180578A1/fr
Priority to PCT/EP2001/009015 priority patent/WO2002014654A1/fr
Priority to JP2002519765A priority patent/JP4726389B2/ja
Priority to DE50108476T priority patent/DE50108476D1/de
Priority to EP01962905A priority patent/EP1309773B1/fr
Priority to ES01962905T priority patent/ES2255567T3/es
Priority to US10/344,730 priority patent/US7201564B2/en
Publication of EP1180578A1 publication Critical patent/EP1180578A1/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Withdrawn legal-status Critical Current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
    • F01D5/14—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 blades of the rearmost stages, each with a radially outer foot area, a radially inner head area and one between Radial cooling air duct running at the top and bottom, into the cooling air in an inlet opening in the foot area can be introduced and through an outlet opening in the head area is at least partially reusable.
  • a hot gas stream driving a turbine is generated by the stationary Turbine guide vanes to the turbine blades, the disks rotating on a central turbine axis are attached, directed.
  • a circular arrangement of Turbine guide vanes with their radially outer root areas attached to a stationary turbine housing wall alternate with an arrangement of turbine blades on a rotating disc.
  • the radial inner head areas of the turbine guide vanes border on one U-shaped inner ring, one on its outside Has labyrinth seal against the flow around the U-ring sealed with hot gas.
  • the problem here is that the U-shaped ring is made of and cost reasons mostly from a little temperature resistant Material exists.
  • the cooling air When flowing through the turbine guide vane the cooling air usually heats up to the maximum permissible temperature of the turbine guide vane.
  • the cooling air therefore already has it when it flows into the U-ring a fairly high temperature and can with the low Amounts of cooling air required for cooling the turbine guide vane a rear stage compared to the other turbine guide vane stages not very warm, would be enough do not provide sufficient cooling of the U-ring.
  • This is also problematic because the in through the U-ring and the cavity formed in the turbine blade head region Cooling air is discharged after flowing through the cavity and towards the rear, largely uncooled, heat sensitive turbine blade disk flows.
  • the object of the present invention is therefore an arrangement of turbine guide vanes to create a lower Requires cooling air, while the U-shaped Ring is sufficiently cooled.
  • the cooling air duct has a has radial inner channel through which the cooling air from the foot area flows to the head area and one to the inner channel adjacent outer channel, which at least partially the inner channel surrounds the circumference, which communicates with the inner channel and which has an outlet opening in the foot area, a portion of cooling air in the direction through the outer duct Flows back foot area and flows out through the outlet opening.
  • cooling air duct By dividing the cooling air duct into the inner and outer duct it is achieved that the cooling air first through the inner duct flows and partially at the foot area to cool the U-shaped Ring flows out and partly again after the diversion flows back through the outer channel.
  • the inner channel will flowed through by the total amount of cooling air and less Flow of cooling air flows in the form of a counterflow.
  • the cooling air flowing back in a rapid flow isolates on the one hand the inner duct and allows the cooling air to the outflow point in the U-ring at the head area a low Has temperature without using large amounts of cooling air should be.
  • the cooling air flowing back cools the side walls of the cooling air duct and thus the surrounding ones Areas of the turbine guide vane that support the load Areas of the turbine guide vane are.
  • the walls of the Turbine blades that surround 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 small amounts of cooling air both the turbine guide vane and the U-shaped ring are sufficiently cooled become.
  • the outer channel has the inner channel practically on all sides on the circumference surrounds the heat radiation through the inner channel guided cooling air from almost all sides of the part the cooling air, which can be conducted through the outer duct, is removed. Because of the large radiation area is a large one Heat transfer possible in a short time. The one arriving in the head area Cooling air thus has a very low temperature and can optimally cool the U-shaped ring.
  • the inner channel has at least one communication hole, can pass through the cooling air into the outer duct, the cooling air is accelerated very strongly at the drilling site. This improves the cooling properties of the cooling air in the Outer channel, because of the higher speed more heat can be included.
  • a long cooling air path inside the turbine guide vane and thus a good utilization of the cooling air is achieved if the inner channel at least at a head end area has a communication hole.
  • the cooling air can the cooling air pipe over almost the entire length between the head and shield the foot area from the hot shovel wall, see above that emerges in the head region of the turbine guide vane Cooling air even with a low cooling air flow in the inner duct has a sufficiently low temperature to make the U-shaped Ring cool well.
  • the cooling air flow flowing back in the outer duct cools the surrounding areas of the turbine guide vane at the same time.
  • the turbine guide vane at the foot area has an outlet opening in a trailing edge area, which is connected to the outer channel.
  • a trailing edge area which is connected to the outer channel.
  • the arrangement of the outlet opening in the rear edge area prevents penetration of inflowing hot gas that would cause damage.
  • the fact that the outlet openings for the cooling air flowing through the outer duct Base area of the turbine guide vane are housed the cooling air goes a very long way inside the turbine vane and can also be used with smaller amounts of cooling air absorb a lot of thermal energy from the turbine guide vane and lead to the outside without the air in the inner channel would be heated.
  • the speed is and the type of flow of cooling air flowing around the total channel length approximately the same size and thus also the Heat dissipation. This ensures an even cooling performance guaranteed.
  • the inner duct is a cooling air guide tube which can be inserted into the cooling air duct is that with a distance to the inner walls of the Cooling air duct is arranged and the outer duct through the Space between the cooling air guide tube and the inner walls of the cooling air duct is formed.
  • the production of the cooling channel is simplified.
  • the cooling air guide tube can after casting be used in the cooling air duct.
  • the outer channel exists then from that extending around the cooling air guide tube Gap.
  • the thickness of the space that the Distance of the cooling air guide tube from the side walls of the cooling air duct can be adjusted as required. The narrower the gap, the greater the speed the cooling air forced through. By a increasing cooling air speed increases their ability for heat dissipation.
  • the cross section of the outer channel is like this is chosen that the cooling air flows quickly through the duct and thus sufficient cooling is guaranteed.
  • the task also relates to a process for Production of a turbine guide vane.
  • the task is solved by a casting process for the production an arrangement of turbine guide vanes in which a Core is used which is the cooling air duct of the turbine guide vane generated, with the core having a smaller cross section has, as usual cores for the casting of turbine guide vanes, after casting in the cooling air duct with at least one Cooling air guide tube provided with communication hole at a distance to the inner walls of the cooling air duct, and into the wall in the rear edge area of the foot area of the Turbine guide vane up to the outer contour of the turbine guide vane through openings are introduced.
  • the shape of the blade core for the Casting can be reduced in size compared to conventional casting cores. Since the resulting cooling channel is therefore smaller, the wall thickness increases the turbine blade, in particular to the leading edge strongly towards. The cast is therefore uncritical in view Wall thicknesses considerably simplified.
  • a cooling air guide tube is used. Between the cooling air duct and the cooling channel inner wall is only a narrow one External channel that surrounds the cooling air guide tube in a ring.
  • the cooling air is thus not heated up as much. A smaller amount of cooling air is sufficient out.
  • the cooling of the turbine guide vane is with the relatively low temperatures especially in the rear Levels sufficient.
  • Fig. 1 shows a perspective view of a turbine guide vane 1 of the last steps.
  • the foot area 2 which has retaining projections 24, becomes the turbine guide vane 1 on an inner wall, not shown cylindrical turbine casing attached.
  • the turbine guide vane 1 Extends from there the turbine guide vane 1 with its airfoil 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 forms the head area 3, which is a plateau 25 and a radially inner one with respect to the turbine axis 30 has arcuate recess 26.
  • At this head area 3 is a U-shaped by means of rail-like holding projections 27 Ring 19 coupled.
  • the holding projections 27 engage in Retaining grooves 28 of the U-shaped ring 19.
  • One is located radially on the inside of the U-shaped ring 19 Labyrinth seal 21. This seals the when the Turbine rotating about the central turbine axis 31, adjacent underlying turbine blade disc 22, the Turbine blades, not shown, is occupied against a direct flow of hot gas 17 from.
  • the airfoil 18 has a radial, cylindrical shape Cooling air duct 4, which is continuous from an inlet opening 36 of the cooling air 23 in the foot region 2 of the turbine guide vane 1 up to its outlet opening 35 of the cooling air Head region 3 of the turbine guide vane 1 runs. He has a cross-sectional contour 34 in the area of the airfoil 18 and the foot region 2 of the outer contour 16 of the airfoil 18 resembles. The cross-sectional contour 34 of the cooling air duct 4 remains when looking from the foot area 2 to before Main area 3 can get substantially in shape however decrease in size. When the cooling air duct enters 4 in the head region 3, the cross section 34 narrows Form of a circumferential step 33.
  • This narrowed cross section 34 is then up to the recess 26 in the head area 3, in the the outlet opening 35 of the cooling channel 4 into the cavity 20 approximately maintained.
  • the cooling air duct 4 is a cylindrical cooling air guide tube 13 inserted approximately in the center.
  • the cooling air guide tube 13 has an almost constant elliptical cross section 15.
  • the cooling air guide tube is held 13 at the head region 3 of the turbine guide vane 1 essentially in that it is up to the revolving stage 33 with a cross section 15 adapted to the transition is sufficient or even in the head region 3 in the narrowed cross section 34 of the cooling air duct 4 is used.
  • the cooling air guide tube 13 for example, by on side walls 8 of the cooling air duct 4 attached spacers 37 held in the middle.
  • the cooling air duct 4 can when casting the turbine blade 1 cast directly by inserting a casting core become.
  • the cooling air guide tube 13 is cast in the Cooling air duct 4 used.
  • the cooling air 23 enters the inlet opening 36 of the cooling air guide tube 13, which extends up to an upper side 32 of the foot region 2 of the turbine guide vane 1 is sufficient.
  • the cooling air 23 then flows through the cooling air guide tube 13 to a communication hole 10.
  • a cooling air flow component 42 continues to flow to the head region 3 of the turbine blade 1 and there through the outlet opening 35 in the Cavity 20.
  • Another cooling air flow portion 41 flows from Cooling air guide tube 13 through a communication hole 10 in an outer channel 9 between the cooling air guide tube 13 and the cooling air channel 4 and there in the opposite direction Foot area 2, as shown in Fig.2. Through the narrowed Bores 10 the cooling air portion 41 flows accelerated the cooling channel inner wall 8.
  • 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 area 5 flows into the cooling air guide tube 13 split into two cooling air flow portions, the redirected Cooling air flow 41 through the holes 10 on the head side End region 6 flows into the outer channel 9 and at the outlet opening 12 flows out again, and that to the U-shaped ring 19 cooling air stream 42 flowing out.
  • FIG 3 shows the development of the temperature T of the cooling air flow components 41, 42, while the turbine guide vane 1 in the longitudinal direction 31 to an end length 1 of the cooling air duct Flow through 4.
  • the maximum temperature Tmax is from continuous current 42 is not reached, causing the U-shaped Ring can be cooled sufficiently.
  • the other part of the cooling air 41 takes the greater part of the heat with and conveys it out of the turbine blade without the heat can damage the temperature-sensitive areas.
  • the whole Cooling air volume 23, the sum of both electricity 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)
EP00117667A 2000-08-16 2000-08-16 Aubes statoriques pour une turbomachine Withdrawn EP1180578A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP00117667A EP1180578A1 (fr) 2000-08-16 2000-08-16 Aubes statoriques pour une turbomachine
PCT/EP2001/009015 WO2002014654A1 (fr) 2000-08-16 2001-08-03 Dispositif d'aubes directrices de turbine
JP2002519765A JP4726389B2 (ja) 2000-08-16 2001-08-03 タービン静翼
DE50108476T DE50108476D1 (de) 2000-08-16 2001-08-03 Anordnung von turbinenleitschaufeln
EP01962905A EP1309773B1 (fr) 2000-08-16 2001-08-03 Dispositif d'aubes directrices de turbine
ES01962905T ES2255567T3 (es) 2000-08-16 2001-08-03 Disposicion de alabes directrices de turbina.
US10/344,730 US7201564B2 (en) 2000-08-16 2001-08-03 Turbine vane system

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP1180578A1 true EP1180578A1 (fr) 2002-02-20

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 After (1)

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

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)

Cited By (3)

* 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
EP2471612A1 (fr) * 2010-12-30 2012-07-04 United Technologies Corporation Procédé et noyau de moulage permettant de former un atterrissage pour le soudage d'un déflecteur inséré dans une surface portante
EP2840231A1 (fr) * 2013-08-23 2015-02-25 Siemens Aktiengesellschaft Aube de turbine dotée d'une pale creuse

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Publication number Priority date Publication date Assignee Title
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
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
US8162598B2 (en) * 2008-09-25 2012-04-24 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
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
US9435212B2 (en) * 2013-11-08 2016-09-06 Siemens Energy, Inc. Turbine airfoil with laterally extending snubber having internal cooling system
US11033845B2 (en) * 2014-05-29 2021-06-15 General Electric Company Turbine engine and particle separators therefore
WO2016025056A2 (fr) 2014-05-29 2016-02-18 General Electric Company Moteur de turbine, et épurateurs de particules pour celui-ci
US10132195B2 (en) 2015-10-20 2018-11-20 General Electric Company Wheel space purge flow mixing chamber
US10125632B2 (en) * 2015-10-20 2018-11-13 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
US10280841B2 (en) 2015-12-07 2019-05-07 United Technologies Corporation Baffle insert for a gas turbine engine component and method of cooling
US10577947B2 (en) 2015-12-07 2020-03-03 United Technologies Corporation Baffle insert for a gas turbine engine component
US10337334B2 (en) * 2015-12-07 2019-07-02 United Technologies Corporation Gas turbine engine component with a baffle insert
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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DE1210254B (de) * 1962-03-26 1966-02-03 Rolls Royce Gasturbinentriebwerk mit gekuehlten Turbinen-laufschaufeln
US4218179A (en) * 1977-07-22 1980-08-19 Rolls-Royce Limited Isothermal aerofoil with insulated internal passageway
US4818178A (en) * 1986-02-04 1989-04-04 Marresearch Gesellschaft Fuer Forschung Und Entwicklung Gmbh Process for cooling the blades of thermal turbomachines
US5813827A (en) * 1997-04-15 1998-09-29 Westinghouse Electric Corporation Apparatus for cooling a gas turbine airfoil

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GB976124A (en) * 1962-09-24 1964-11-25 Gen Electric Improvements in compressor or turbine guide vanes
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US3094310A (en) * 1959-12-09 1963-06-18 Rolls Royce Blades for fluid flow machines
DE1210254B (de) * 1962-03-26 1966-02-03 Rolls Royce Gasturbinentriebwerk mit gekuehlten Turbinen-laufschaufeln
US4218179A (en) * 1977-07-22 1980-08-19 Rolls-Royce Limited Isothermal aerofoil with insulated internal passageway
US4818178A (en) * 1986-02-04 1989-04-04 Marresearch Gesellschaft Fuer Forschung Und Entwicklung Gmbh Process for cooling the blades of thermal turbomachines
US5813827A (en) * 1997-04-15 1998-09-29 Westinghouse Electric Corporation Apparatus for cooling a gas turbine airfoil

Cited By (7)

* 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
EP2471612A1 (fr) * 2010-12-30 2012-07-04 United Technologies Corporation Procédé et noyau de moulage permettant de former un atterrissage pour le soudage d'un déflecteur inséré dans une surface portante
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
US11077494B2 (en) 2010-12-30 2021-08-03 Raytheon Technologies Corporation Method and casting core for forming a landing for welding a baffle inserted in an airfoil
US11707779B2 (en) 2010-12-30 2023-07-25 Raytheon Technologies Corporation Method and casting core for forming a landing for welding a baffle inserted in an airfoil
EP2840231A1 (fr) * 2013-08-23 2015-02-25 Siemens Aktiengesellschaft Aube de turbine dotée d'une pale creuse
WO2015024800A1 (fr) * 2013-08-23 2015-02-26 Siemens Aktiengesellschaft Aube de turbine présentant une pale creuse

Also Published As

Publication number Publication date
WO2002014654A1 (fr) 2002-02-21
JP4726389B2 (ja) 2011-07-20
EP1309773B1 (fr) 2005-12-21
JP2004506827A (ja) 2004-03-04
ES2255567T3 (es) 2006-07-01
US7201564B2 (en) 2007-04-10
DE50108476D1 (de) 2006-01-26
US20030180147A1 (en) 2003-09-25
EP1309773A1 (fr) 2003-05-14

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