EP2607629A1 - Aube de turbine caréné dotée d'un port de sortie d'air de refroidissement en bout d'aube et procédé associé de fabrication - Google Patents

Aube de turbine caréné dotée d'un port de sortie d'air de refroidissement en bout d'aube et procédé associé de fabrication Download PDF

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Publication number
EP2607629A1
EP2607629A1 EP11195390.7A EP11195390A EP2607629A1 EP 2607629 A1 EP2607629 A1 EP 2607629A1 EP 11195390 A EP11195390 A EP 11195390A EP 2607629 A1 EP2607629 A1 EP 2607629A1
Authority
EP
European Patent Office
Prior art keywords
outlet port
blade
radial direction
port
extending
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Withdrawn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
EP11195390.7A
Other languages
German (de)
English (en)
Inventor
Thomas Sommer
Brian Wardle
Igor Tsypkaykin
Stefan Retzko
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP11195390.7A priority Critical patent/EP2607629A1/fr
Publication of EP2607629A1 publication Critical patent/EP2607629A1/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Withdrawn legal-status Critical Current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
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding

Definitions

  • the present invention relates to a turbine blade, preferably for a gas turbine, with a blade body, extending in a radial direction between a blade root and a blade tip, wherein the blade body is provided with at least one inner passage for a cooling medium and at least one outlet port to exhaust the cooling medium from the inner cooling medium passage to the outer side of the blade tip.
  • Patent application WO 2005/106206 A1 shows a turbine blade for a gas turbine with a blade body, extending in a radial direction between a blade root and a blade tip.
  • a blade shroud On the blade tip a blade shroud is arranged, and within the blade body an inner passage for a cooling medium, such as air, is arranged, shown as a hole within the blade body extending in radial direction.
  • the hole forms an outlet port, which is arranged on the outer platform of the blade shroud. Cooling medium can be exhausted through the outlet port, which leads to a cooling effect at that portion of the shroud.
  • the outlet port extends along the radial direction in such a way, that the outlet port is perpendicular to the surface formed by the outer platform of the blade shroud.
  • the basic idea of this invention comprises an outlet port for the cooling medium at the tip of the blade, wherein the longitudinal axis of the outlet port is inclined to the radial direction.
  • the outlet port comprises an alignment having a tangential component parallel to the rotating direction.
  • the longitudinal axis of the outlet port is inclined with respect to the radial direction having an inclination angle.
  • the inclined alignment of the port axis leads to an improvement of the pressure behavior of the exhausted cooling medium.
  • the tangential component of the exhaust cooling medium velocity allows the recovery of pumping power.
  • the outlet port extends from the inner cooling medium passage to the outer side of the blade tip in the inclined port axis.
  • the outlet port comprises an inner section extending in the radial direction and passing into a section formed by the outlet port in the inclined port axis.
  • the present invention comprising an outlet port with a longitudinal axis inclined to the radial direction is not limited to an outlet port featuring a single axis, which is inclined to the radial direction.
  • the advantage of the present invention is also achieved, when only a part of the outlet port features a longitudinal axis, which is inclined to the radial direction.
  • the outlet port may comprise an inner section extending in the radial direction and passing into a section formed by the inventive outlet port featuring a longitudinal axis, which is inclined to the radial direction. In both cases, the advantage of the present invention, namely an improved recovery of pumping power, can be obtained.
  • the turbine blade comprises a blade shroud comprising an outer platform, wherein the outlet port leads into the outer platform.
  • the outer platform is an integral part provided with the blade body, and at least one outlet port passes through the blade shroud and leads into the surface of the outer platform.
  • Another preferred embodiment comprises an inclination angle between the inclined port axis and the radial direction, which amounts 20° to 80°, preferred 40° to 60° and most preferred 45°.
  • the outlet port may feature at least in its end section a curvature, and the port axis, which is inclined to the radial direction, represents the tangential axis in the transition of the outlet port to the surface of the blade body, in particular the surface of the blade shroud within the outer platform.
  • the inclination angle amounts between 30° and 50°, in particular 35° to 45°, the recovery of pumping power has shown optimal results.
  • the turbine blade features an airfoil cross section having a pressure side and a suction side, the outlet port being inclined into the direction of the pressure side.
  • the outlet port is inclined in the rotational direction of the turbine blade.
  • the length of the outlet port is defined by the distance between the inner passage for the cooling medium and the surface of the blade tip, or the surface of the outer platform of the blade shroud, respectively.
  • the diameter refers to an outlet port with a circular cross section.
  • the length of the outlet port amounts at least two times the diameter of the outlet port.
  • the side rails extend radially outward from the platform and preferably delimitate the outer platform at least lateral to the rotation direction of the turbine.
  • the side rails increase the stiffness of the blade shroud and decrease the deformation and bending in the radial outward direction with the time of turbine operation.
  • the side rails improve the dynamic behavior in the gap between the blade shroud and the stator ring of the turbine. Consequently, the advantage of the inventive arrangement of the outlet port combined with side rails in the blade shroud enhances the positive effects of the invention.
  • At least one added material section is applied to the port area of the outlet port on the blade tip, wherein the outlet port is formed in the added material section.
  • the objective of the present invention is furthermore achieved by a method for providing a turbine blade for a gas turbine with a blade body, extending in a radial direction between the blade root and the blade tip, wherein the blade body is provided with at least one inner passage for a cooling medium and at least one outlet port to exhaust the cooling medium from the inner passage to the outer side of the blade tip, and wherein the method comprises the steps of applying at least one added material section to the port area of the outlet port and forming an outlet port in the added material section having a longitudinal axis being inclined to the radial direction.
  • An added material section can be applied to the blade tip, which represents the port area of the outlet port, advantageously featuring the same material as the material of the blade body.
  • the forming of an outlet port may be done in the added material section by drilling a through hole.
  • the at least one added material section can be applied to the port area of the outlet port by means of welding, preferably build-up welding.
  • This build-up welding technology forms a well-known technology for repairing turbine blades.
  • the outlet port is formed by applying at least one added material section to the port area by forming a hole in the added material section extending in a radial direction and being aligned with the section of the outlet port, and arranging a closure means on the added material section which closes the outer mouth of the hole, and forming a lateral hole into the added material section extending along a port axis inclined to the radial direction and thus featuring an intersection with the hole extending in radial direction.
  • the hole-forming in the added material section can be performed mechanically or by EDM-technology or by ECM-technology or other suitable means.
  • FIGS 1 and 2 show a turbine blade 1 in a perspective view ( Figure 1 ) and in a side-view ( Figure 2 ).
  • the turbine blade 1 features a blade body 10 and the blade body 10 extends in a radial direction 11 between a blade root 12 and a blade tip 13.
  • a blade shroud 14, is arranged at the blade tip 13, the blade shroud 14 contributing to a controlled and a minimized leakage flow in the gap between the blade tip 13 and a stator casing of the turbine.
  • the blade shroud 14 arranged on the blade tip 13 minimizes vibration amplitudes of the turbine blade 1.
  • the blade shroud 14 shown in the figures comprises an outer platform 18 extending in a plane essentially parallel to the stator opposite of the blade tip 13 and the outer platform 18 may comprise two or more fins 23.
  • a passage 15 for a cooling medium is arranged within the blade body 10, and the passage 15 is pressurized by cooling air, for example.
  • At least one outlet port 16, as shown in figure 2 forms a channel between the passage 15 and the outer platform 18.
  • Figure 3 shows a top-view of the turbine blade 1 with the blade body 10, extending between the blade root 12 and the blade tip 13.
  • An outlet port 16 is arranged in the blade body 10, which breaks through the blade shroud 14.
  • the embodiment of the turbine blade 1 shows an outer platform 18 which features side rails 19 extending radially outward from the platform 18 and delimiting the outer platform 18 laterally to the rotation direction 20 of the turbine.
  • the outlet port 16 shown in figure 3 , features a longitudinal axis 17 which is inclined to the radial direction 11, as shown in the cross-sectional view of the following figure 4 .
  • Figure 4 shows a cross sectional view of a turbine blade 1 comprising a blade body 10.
  • an inner section 16' of an outlet port 16 is shown within the blade body 10.
  • the inner section 16' of the outlet port 16 extends in a radial direction 11, and in the blade tip 13 of the outlet port 16 extends along a port axis 17, which is inclined towards the radial direction 11.
  • the outlet port 16 features the port axis 17 inclined towards the radial direction 11 passing through the outer platform 18 of the blade shroud 14.
  • the inclination angle is indicated with ⁇ , and the port axis 17 is inclined to a pressure site P, forming the opposite side of the suction side S of the blade body 10.
  • the inclination of the port axis 17 and thus the outlet port 16 results to an improved recovery of pumping power.
  • the outlet port 16 features a diameter D and a length L, wherein the relation between D/L features the value 2.
  • Figure 5 shows another embodiment of the turbine blade 1 with a blade body 10 and a blade shroud 14 arranged on the blade tip 13.
  • An inner passage 15 for the cooling medium is shown within the blade body 10 and an outlet port 16 forms a connection between the cooling medium chamber 15 and the outer platform 18 of the blade shroud 14.
  • the outlet port 16 extends along the radial direction 11, and the turbine blade 1 comprising the aforementioned features forms a turbine blade 1 according to the state of the art.
  • an added material section 21 is applied to the area of the outlet port 16.
  • the added material section 21 is welded on the surface of the outer platform 18 and features an extending outlet port 16", which is arranged in a radial direction 11 and forms a hole which elongates the outlet port 16' in the radial direction 11.
  • the extending outlet port 16" is drilled into the added material section 21, either by means of mechanical drilling or by means of EDM-technology or ECM-technology.
  • a closure means 22 is applied to the mouth of the extending outlet port 16" in the added material section 21.
  • the extending outlet port 16" is closed in the radial direction 11.
  • an inclined outlet port 16"' is arranged in the added material section 21 along a port axis 17, which is inclined to the radial direction 11 and the inclined outlet port 16"' forms an intersection with the extending outlet port 16".

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11195390.7A 2011-12-22 2011-12-22 Aube de turbine caréné dotée d'un port de sortie d'air de refroidissement en bout d'aube et procédé associé de fabrication Withdrawn EP2607629A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11195390.7A EP2607629A1 (fr) 2011-12-22 2011-12-22 Aube de turbine caréné dotée d'un port de sortie d'air de refroidissement en bout d'aube et procédé associé de fabrication

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11195390.7A EP2607629A1 (fr) 2011-12-22 2011-12-22 Aube de turbine caréné dotée d'un port de sortie d'air de refroidissement en bout d'aube et procédé associé de fabrication

Publications (1)

Publication Number Publication Date
EP2607629A1 true EP2607629A1 (fr) 2013-06-26

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EP11195390.7A Withdrawn EP2607629A1 (fr) 2011-12-22 2011-12-22 Aube de turbine caréné dotée d'un port de sortie d'air de refroidissement en bout d'aube et procédé associé de fabrication

Country Status (1)

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EP (1) EP2607629A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3034789A1 (fr) 2014-12-16 2016-06-22 Alstom Technology Ltd Aube rotative de turbine à gaz et turbine à gaz avec une telle aube
WO2017020178A1 (fr) 2015-07-31 2017-02-09 General Electric Company Agencements de refroidissement dans des aubes de turbine
JP2017198202A (ja) * 2016-04-14 2017-11-02 ゼネラル・エレクトリック・カンパニイ タービン翼の先端シュラウドの冷却用シールレールのためのシステム
US10301943B2 (en) 2017-06-30 2019-05-28 General Electric Company Turbomachine rotor blade
US10502069B2 (en) 2017-06-07 2019-12-10 General Electric Company Turbomachine rotor blade
US10577945B2 (en) 2017-06-30 2020-03-03 General Electric Company Turbomachine rotor blade
US10590777B2 (en) 2017-06-30 2020-03-17 General Electric Company Turbomachine rotor blade
US11060407B2 (en) 2017-06-22 2021-07-13 General Electric Company Turbomachine rotor blade

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5847104A (ja) * 1981-09-11 1983-03-18 Agency Of Ind Science & Technol ガスタ−ビンのタ−ビン動翼
GB1605335A (en) * 1975-08-23 1991-12-18 Rolls Royce A rotor blade for a gas turbine engine
DE19904229A1 (de) * 1999-02-03 2000-08-10 Asea Brown Boveri Gekühlte Turbinenschaufel
EP1041247A2 (fr) * 1999-04-01 2000-10-04 General Electric Company Cirquit de refroidissement pour une aube d'une turbine à gaz et sa plateforme de tête
EP1219781A2 (fr) * 2000-12-22 2002-07-03 ALSTOM Power N.V. Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine
GB2384275A (en) * 2001-09-27 2003-07-23 Rolls Royce Plc Cooling of blades for turbines
WO2005106206A1 (fr) 2004-04-30 2005-11-10 Alstom Technology Ltd Enveloppe pour aube d'une turbine a gaz
EP1749967A2 (fr) * 2005-08-02 2007-02-07 Rolls-Royce plc Dispositif de refroidissement de turbine à gaz
US20070065283A1 (en) * 2005-05-16 2007-03-22 Masaru Sekihara Gas turbine rotor blade, gas turbine using the rotor blade, and power plant using the gas turbine
EP2149675A2 (fr) * 2008-07-29 2010-02-03 General Electric Company Aube de turbine et procédé de sa fabrication

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1605335A (en) * 1975-08-23 1991-12-18 Rolls Royce A rotor blade for a gas turbine engine
JPS5847104A (ja) * 1981-09-11 1983-03-18 Agency Of Ind Science & Technol ガスタ−ビンのタ−ビン動翼
DE19904229A1 (de) * 1999-02-03 2000-08-10 Asea Brown Boveri Gekühlte Turbinenschaufel
EP1041247A2 (fr) * 1999-04-01 2000-10-04 General Electric Company Cirquit de refroidissement pour une aube d'une turbine à gaz et sa plateforme de tête
EP1219781A2 (fr) * 2000-12-22 2002-07-03 ALSTOM Power N.V. Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine
GB2384275A (en) * 2001-09-27 2003-07-23 Rolls Royce Plc Cooling of blades for turbines
WO2005106206A1 (fr) 2004-04-30 2005-11-10 Alstom Technology Ltd Enveloppe pour aube d'une turbine a gaz
US20070065283A1 (en) * 2005-05-16 2007-03-22 Masaru Sekihara Gas turbine rotor blade, gas turbine using the rotor blade, and power plant using the gas turbine
EP1749967A2 (fr) * 2005-08-02 2007-02-07 Rolls-Royce plc Dispositif de refroidissement de turbine à gaz
EP2149675A2 (fr) * 2008-07-29 2010-02-03 General Electric Company Aube de turbine et procédé de sa fabrication

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10036284B2 (en) 2014-12-16 2018-07-31 Ansaldo Energia Switzerland AG Rotating gas turbine blade and gas turbine with such a blade
EP3034789A1 (fr) 2014-12-16 2016-06-22 Alstom Technology Ltd Aube rotative de turbine à gaz et turbine à gaz avec une telle aube
WO2017020178A1 (fr) 2015-07-31 2017-02-09 General Electric Company Agencements de refroidissement dans des aubes de turbine
EP3329099A4 (fr) * 2015-07-31 2019-07-24 General Electric Company Agencements de refroidissement dans des aubes de turbine
US10184342B2 (en) 2016-04-14 2019-01-22 General Electric Company System for cooling seal rails of tip shroud of turbine blade
EP3244011A3 (fr) * 2016-04-14 2017-12-27 General Electric Company Système de refroidissement de rails d'étanchéité de carénage d'extrémité d'aube de turbine
CN107435561A (zh) * 2016-04-14 2017-12-05 通用电气公司 用于冷却涡轮叶片的尖端叶冠的密封导轨的系统
JP2017198202A (ja) * 2016-04-14 2017-11-02 ゼネラル・エレクトリック・カンパニイ タービン翼の先端シュラウドの冷却用シールレールのためのシステム
CN107435561B (zh) * 2016-04-14 2022-04-12 通用电气公司 用于冷却涡轮叶片的尖端叶冠的密封导轨的系统
US10502069B2 (en) 2017-06-07 2019-12-10 General Electric Company Turbomachine rotor blade
US11060407B2 (en) 2017-06-22 2021-07-13 General Electric Company Turbomachine rotor blade
US10301943B2 (en) 2017-06-30 2019-05-28 General Electric Company Turbomachine rotor blade
US10577945B2 (en) 2017-06-30 2020-03-03 General Electric Company Turbomachine rotor blade
US10590777B2 (en) 2017-06-30 2020-03-17 General Electric Company Turbomachine rotor blade

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