EP1726783B1 - Aube creuse de rotor pour la turbine d'un moteur à turbine à gaz, équipée d'une baignoire - Google Patents

Aube creuse de rotor pour la turbine d'un moteur à turbine à gaz, équipée d'une baignoire Download PDF

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Publication number
EP1726783B1
EP1726783B1 EP06113886A EP06113886A EP1726783B1 EP 1726783 B1 EP1726783 B1 EP 1726783B1 EP 06113886 A EP06113886 A EP 06113886A EP 06113886 A EP06113886 A EP 06113886A EP 1726783 B1 EP1726783 B1 EP 1726783B1
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EP
European Patent Office
Prior art keywords
blade
wall
side wall
rim
intrados
Prior art date
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Active
Application number
EP06113886A
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German (de)
English (en)
French (fr)
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EP1726783A1 (fr
Inventor
Pascal Deschamps
Chantal Giot
Thomas Potier
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Publication date
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Publication of EP1726783A1 publication Critical patent/EP1726783A1/fr
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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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator

Definitions

  • the invention relates to a hollow rotor blade for the turbine of a gas turbine engine, in particular for a high pressure type turbine.
  • the present invention relates to the production of a hollow blade of the type which comprises an internal cooling passage, an open cavity located at the free end of the blade and delimited by a bottom wall extending over the entire free end of the blade and a flange extending between the leading edge and the trailing edge along at least the upper surface, and cooling channels connecting the internal cooling passage and the free end on the side of the intrados wall, the cooling channels being inclined relative to the intrados wall, the intrados wall having a projecting end portion whose outer face is inclined with respect to the outer face of the intrados wall, the bottom wall being connected to the intrados wall at the location of the end portion and the cooling channels being disposed in the end portion parallel to the an outer face of the end portion so that they open on the top of the end portion towards the free end of the blade, at least a portion of the top of the end portion being in the same plane as the outer face of the bottom wall, so that at least a portion of the cooling channels open from the intrados wall at the front of the cavity.
  • Cooling channels of this type are intended to cool the free end of the blade because they allow to discharge a jet of cooling air from the internal cooling passage, towards the end of the blade at the level of the blade. the upper end of the outer face of the intrados wall.
  • This air jet creates "thermal pumping", that is to say a decrease in the temperature of the metal by absorption of calories in the heart of the metal wall, and a cooling air film that protects the end of the vanes on the intrados side.
  • the blades are hollow to allow their cooling by the air present in an internal cooling passage.
  • These cooling channels located on the side of the intrados wall thus allow the outlet, from the internal cooling passage, of a jet of air colder than that surrounding the intrados wall, this air jet forming a cooling air film located on the outside face of the intrados wall, which is sucked in the direction of the extrados wall, passing over the end of the blade.
  • This solution therefore requires a significant material thickness, either for the bottom wall of the cavity or for the rim of the cavity, so as not to call into question the performance of thermomechanical resistance at the end of the blade.
  • this solution greatly limits the flow of cooling air that reaches the top of the rim because most of the flow exits the internal cooling passage through the first section of the cooling channels and enters directly into the cavity without success. on the outside face of the intrados wall.
  • thermomechanical resistance at the end of the blade requires a significant material thickness, either for the bottom wall of the cavity or for the rim of the cavity, so as not to call into question the performance of thermomechanical resistance at the end of the blade.
  • the document FR 2 858 650 a proposed a solution (see figure 5 ) which consists in providing a reinforcement of material between the rim and the bottom wall of the cavity along at least a portion of the intrados wall, whereby said rim is widened at its base adjacent to said wall; bottom so that the cooling channels open near the top of the rim without altering the mechanical strength of the end of the blade. In this way, by the presence of the material reinforcement, the cooling channels can thus emerge closer to the top of the rim without modifying the distance between these cooling channels and the bottom wall of the cavity.
  • the document US 2002/0182074 discloses a turbine blade whose end is in the form of a bath with a bottom surrounded by flanges, the intrados wall of the flange located at the intrados comprising an excrescence traversed by cooling channels parallel to the outer surface of this protrusion.
  • the intrados flange is such that the upper surface of this protrusion is in the same plane as the bottom of the bath.
  • the present invention seeks to solve the aforementioned problems.
  • the present invention aims to provide a hollow rotor blade for the turbine of a gas turbine engine, of the type mentioned above, to cool the end of the blade sufficiently to improve its reliability without reducing the aerodynamic and thermomechanical performance of dawn.
  • the inner face of the rim of the upper surface is inclined by widening the flange towards the free end of the blade.
  • This solution also has the additional advantage of allowing, in addition to feeding the outlet of the cooling channels to the free end of the blade, to achieve, in that the outer face of the end portion is sloping, an intrados surface of the dawn which is made concave at the top of the blade.
  • This particular shape is preferably present all along the profile, from the leading edge to the trailing edge. It prevents the flow in the game at the top of dawn. Indeed, the inclination of the wall towards the intrados, at the top of the blade, makes it possible to cause a strong detachment of the boundary layer at the top of the blade. Thus, the passage section "seen" by the flow between the head of the blade and the housing will be all the lower as the separation of the boundary layer will be important: thus reduces the flow "lost" in the gap between the blade head and the crankcase.
  • this projecting end portion with its inclined outer face provides not only thermal but also hydraulic improvements at the blade tip, and a mechanical reinforcement of the blade tip at the location of the cavity open or "bathtub".
  • the outer face of the bottom wall is substantially perpendicular to the intrados wall and the extrados wall, that is to say that the outer face of the bottom wall has a parallel orientation to the axis of dawn, which can be described as horizontal.
  • the outer face of the bottom wall is inclined with respect to the intrados wall and the extrados wall, forming an acute angle with the rim of the cavity extending the extrados wall.
  • the outer face of the bottom wall moves away from the free end of the blade-or approaches the axis of the blade-from the pressure wall to the extrados wall.
  • Cooling air flows inside the blade from the bottom of the blade root 12 in the radial (vertical) direction towards the free end 14 of the blade (in high on the figure 1 ), then this cooling air escapes through an outlet to join the main gas flow.
  • this cooling air circulates in an internal cooling passage 24 situated inside the vane 10 and which ends at the free end 14 of the vane at the level of through bores 15.
  • the body of the blade is profiled so that it defines a lower surface wall 16 (on the left in all the figures) and an extrados wall 18 (on the right in all the figures).
  • the intrados wall 16 has a generally concave shape and is the first face to the flow of hot gases, that is to say the gas pressure side, while the extrados wall 18 is convex and is presented by following the flow of hot gases, that is to say the suction side of the gas.
  • intrados and extrados walls 18 are joined at the location of the leading edge 20 and at the location of the trailing edge 22 which extend radially between the free end 14 of the blade and the top of the foot 12 of dawn.
  • the internal cooling passage 24 is delimited by the inner face 26a of a bottom wall 26 which extends over the entire free end 14 of the blade, between the intrados wall 16 and the extrados wall 18, from the leading edge 20 to the trailing edge 22.
  • the through holes 15 are distributed so as to optimize the cooling, from the leading edge 20 to the edge of leak 22, radially crossing the entire thickness of the bottom wall 26.
  • the intrados and extrados walls 16, 18 form the rim 28 of a "bath" or open cavity 30 in the opposite direction to the internal cooling passage 24, radially outward (upwards in all figures).
  • This rim 28 is formed of an extrados rim 281 and a lower face flange 282 respectively extending radially outwards (upwards in all the figures) the extrados wall 18 and the lower surface wall. 16, beyond the bottom wall 26 and to the free end 14 of the blade.
  • this open cavity 30 is therefore delimited laterally by the inner face of this flange 28 and in the lower part by the outer face 26b of the bottom wall 26.
  • the flange 28 thus forms a thin wall along the profile of the blade which protects the free end 14 of the blade 10 from contact with the corresponding annular surface of the turbine casing.
  • inclined cooling channels 32 pass through the intrados wall 16 to connect the internal cooling passage 24 to the outside face of the intrados wall 16, below the outer face 28a of the intrados flange 282.
  • These cooling channels 32 are inclined so that they open towards the top 28b of the lower edge 282 in order to cool as much as possible this vertex 28b, along the intrados wall 16, or more precisely the along the outer face 28a of the underside 282.
  • the intrados wall 16 has a projecting end portion 34 whose external face is inclined with respect to the outside face of the intrados wall 16, the cooling channels 32 being arranged through this end portion 34.
  • the intrados wall 16 is outwardly projecting at the location of the end portion 34 located at the free end 14 of the blade, so that the outer face of the end portion 34 is inclined is forms an acute angle ⁇ with the radial direction (vertical on the figures 7 and 8 ) of the outer face of the remainder of the intrados wall 16, this angle ⁇ being preferably between 0 and 45 °, in particular between 10 and 35 °, advantageously between 15 and 30 °, and preferably of the order 30 °.
  • This end portion 34 extends over a height such that the bottom wall 26 is connected to the intrados wall 16 at the location of the end portion 34, the apices of the bottom wall 26 and the end portion 34 being aligned.
  • the base of the end portion 34, opposite to the free end 14 is located at a location radially between the inner face 26a of the bottom wall 26 and 75% of the height of the lower surface. 16 from the 12th foot of dawn.
  • cooling channels 32 are always inclined but in this configuration according to the invention, since they pass through the end portion 34, they can lead directly to the bottom of the open cavity 30 forming a bath through the portion of end 34 all the way up.
  • the variant represented on the figure 8 is only different from the figure 7 in that the bottom wall 26 is no longer orthogonal (horizontal) with respect to the intrados and extrados walls 18, but the bottom wall 26 is inclined. More precisely, the outer face 26b of the bottom wall 26 of the open cavity 30 forms an acute angle, in other words less than 90 °, with the outer face 28a of the extrados rim 281 or even of the extrados wall 18 .
  • This configuration allows the cooling air from the channels 32 (arrow 33) to be directed inside the open cavity 30 to the bottom wall 26, coming to combine with the cooling air from holes 15.
  • the top of the end portion 34 is orthogonal to the intrados and extrados walls 16, in a direction parallel to the top of the extrados rim 281.
  • the extrados rim 281 forms a wall located in the radial extension of the extrados wall 18, its outer face 28a being vertical ( figures 7 and 8 ).
  • the extrados rim 281 has an inner face 28c, turned towards the intrados wall 16 and facing the open cavity 30, not vertical but extending inclined, forming an acute angle, that is to say less than 90 °, with the outer face 26b of the bottom wall 26, or with the extrados wall.
  • the upper edge 281 is therefore wider at its top 28b.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06113886A 2005-05-13 2006-05-12 Aube creuse de rotor pour la turbine d'un moteur à turbine à gaz, équipée d'une baignoire Active EP1726783B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0504811A FR2885645A1 (fr) 2005-05-13 2005-05-13 Aube creuse de rotor pour la turbine d'un moteur a turbine a gaz, equipee d'une baignoire

Publications (2)

Publication Number Publication Date
EP1726783A1 EP1726783A1 (fr) 2006-11-29
EP1726783B1 true EP1726783B1 (fr) 2008-07-16

Family

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Family Applications (1)

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EP06113886A Active EP1726783B1 (fr) 2005-05-13 2006-05-12 Aube creuse de rotor pour la turbine d'un moteur à turbine à gaz, équipée d'une baignoire

Country Status (5)

Country Link
US (1) US7351035B2 (zh)
EP (1) EP1726783B1 (zh)
CN (1) CN1861988B (zh)
DE (1) DE602006001785D1 (zh)
FR (1) FR2885645A1 (zh)

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FR2907157A1 (fr) * 2006-10-13 2008-04-18 Snecma Sa Aube mobile de turbomachine
CN101493017A (zh) * 2007-09-28 2009-07-29 通用电气公司 用于涡轮机的气冷式叶片
US8206108B2 (en) * 2007-12-10 2012-06-26 Honeywell International Inc. Turbine blades and methods of manufacturing
GB2461502B (en) * 2008-06-30 2010-05-19 Rolls Royce Plc An aerofoil
US20100135822A1 (en) * 2008-11-28 2010-06-03 Remo Marini Turbine blade for a gas turbine engine
US8092178B2 (en) * 2008-11-28 2012-01-10 Pratt & Whitney Canada Corp. Turbine blade for a gas turbine engine
US8182223B2 (en) * 2009-02-27 2012-05-22 General Electric Company Turbine blade cooling
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US8585356B2 (en) * 2010-03-23 2013-11-19 Siemens Energy, Inc. Control of blade tip-to-shroud leakage in a turbine engine by directed plasma flow
US8500404B2 (en) 2010-04-30 2013-08-06 Siemens Energy, Inc. Plasma actuator controlled film cooling
US8777567B2 (en) 2010-09-22 2014-07-15 Honeywell International Inc. Turbine blades, turbine assemblies, and methods of manufacturing turbine blades
GB201100957D0 (en) * 2011-01-20 2011-03-02 Rolls Royce Plc Rotor blade
FR2982903B1 (fr) 2011-11-17 2014-02-21 Snecma Aube de turbine a gaz a decalage vers l'intrados des sections de tete et a canaux de refroidissement
US9593584B2 (en) 2012-10-26 2017-03-14 Rolls-Royce Plc Turbine rotor blade of a gas turbine
JP6092661B2 (ja) * 2013-03-05 2017-03-08 三菱日立パワーシステムズ株式会社 ガスタービン翼
US9856739B2 (en) 2013-09-18 2018-01-02 Honeywell International Inc. Turbine blades with tip portions having converging cooling holes
US9879544B2 (en) * 2013-10-16 2018-01-30 Honeywell International Inc. Turbine rotor blades with improved tip portion cooling holes
US9816389B2 (en) 2013-10-16 2017-11-14 Honeywell International Inc. Turbine rotor blades with tip portion parapet wall cavities
FR3022295B1 (fr) * 2014-06-17 2019-07-05 Safran Aircraft Engines Aube de turbomachine comportant une ailette anti-tourbillons
US10107108B2 (en) 2015-04-29 2018-10-23 General Electric Company Rotor blade having a flared tip
FR3043715B1 (fr) * 2015-11-16 2020-11-06 Snecma Aube de turbine comprenant une pale avec baignoire comportant un intrados incurve dans la region du sommet de pale
CN106812555B (zh) * 2015-11-27 2019-09-17 中国航发商用航空发动机有限责任公司 涡轮叶片
US10253637B2 (en) * 2015-12-11 2019-04-09 General Electric Company Method and system for improving turbine blade performance
EP3954882B1 (en) * 2016-03-30 2023-05-03 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Variable geometry turbocharger
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US10487679B2 (en) * 2017-07-17 2019-11-26 United Technologies Corporation Method and apparatus for sealing components of a gas turbine engine with a dielectric barrier discharge plasma actuator
KR20190096569A (ko) * 2018-02-09 2019-08-20 두산중공업 주식회사 가스 터빈
JP7093658B2 (ja) * 2018-03-27 2022-06-30 三菱重工業株式会社 タービン動翼及びガスタービン
JP6946225B2 (ja) * 2018-03-29 2021-10-06 三菱重工業株式会社 タービン動翼、及びガスタービン
EP3546702A1 (de) * 2018-03-29 2019-10-02 Siemens Aktiengesellschaft Turbinenlaufschaufel für eine gasturbine
US10787932B2 (en) 2018-07-13 2020-09-29 Honeywell International Inc. Turbine blade with dust tolerant cooling system
KR102590947B1 (ko) * 2021-05-04 2023-10-19 국방과학연구소 선반 스퀼러 팁을 갖는 가스터빈 블레이드

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Also Published As

Publication number Publication date
US7351035B2 (en) 2008-04-01
CN1861988B (zh) 2010-10-06
US20060257257A1 (en) 2006-11-16
FR2885645A1 (fr) 2006-11-17
CN1861988A (zh) 2006-11-15
EP1726783A1 (fr) 2006-11-29
DE602006001785D1 (de) 2008-08-28

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