EP3232000A1 - Plateforme d'une aube comprenant des trous de refroidissement a film et turbomachine associée - Google Patents

Plateforme d'une aube comprenant des trous de refroidissement a film et turbomachine associée Download PDF

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Publication number
EP3232000A1
EP3232000A1 EP16165557.6A EP16165557A EP3232000A1 EP 3232000 A1 EP3232000 A1 EP 3232000A1 EP 16165557 A EP16165557 A EP 16165557A EP 3232000 A1 EP3232000 A1 EP 3232000A1
Authority
EP
European Patent Office
Prior art keywords
platform
projection
region
plane
blade
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Withdrawn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
EP16165557.6A
Other languages
German (de)
English (en)
Inventor
Horst-Michael Dreher
Kunyuan Zhou
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 EP16165557.6A priority Critical patent/EP3232000A1/fr
Publication of EP3232000A1 publication Critical patent/EP3232000A1/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Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the invention relates to a platform of a blade with film cooling on the platform.
  • Blades are exposed to high temperatures in turbomachinery, especially in turbines, especially in gas turbines. This is especially true for the areas that are exposed to the relaxing hot gas. In the areas at the edge between blade attachment and Leitschaufelab gleich form marginal cavities. Although these are not exposed to the main flow of hot gas, high temperatures can still result there. To avoid this, provision is made for a flow in the radial direction from the inside to the outside. For this serves as a cleaning gas or air. This is often about aggressive gases that would cause corrosion, as it were blow out. The associated cooling is another effect. It is often sufficient to prevent the penetration of hot gas.
  • a cooling of a cavity next to the platform is from the EP 2 388 435 A2 known.
  • a platform of a blade for a turbomachine wherein the platform has a plane from which the blade protrudes and protrudes on the side facing away from the blade, a projection which can project when installed in the turbomachine to an axially adjacent Leitschaufelab gleich. This can form a gap between the projection and the Leitschaufelab gleich, which is not exposed to the main gas flow of the gas to be expanded or compressed in the turbomachine.
  • the feature according to which the projection can protrude to an axially adjacent guide vane end is to be explained briefly to avoid misunderstandings. Since the vanes do not rotate, no attachment to the axle can be made at the radially inner end.
  • the vane necessarily has some kind of vane closure in the radial region of the platform of the blades. The vane closure is often not always in a straight line; it may be gradations or the like. Also indentations may result.
  • the projection may protrude approximately into a space that is in the radial direction within the Leitschaufelab gleiches lies.
  • the protrusion may protrude into a space which is radially inward of the vane closure, while at other locations the vane closure is located radially inward. This may be the case, for example, with a graduated vane closure.
  • the projection may protrude into a recess of the Leitschaufelab gleiches. Decisive is the formation of a gap between the projection and Leitschaufelab gleich, which is not exposed to the main gas flow of the gas to be expanded or compressed in the turbomachine. It is understood that the projection, which rotates in operation, the stationary vane end normally must not touch.
  • main gas flow of the gas to be expanded or compressed in the turbomachine is intended to express that there is a flow which is essential for operation.
  • the gas in a gas turbine, the gas must flow, guided by vanes, onto the blades and propel them through relaxation of the gas to obtain mechanical work. This should be the main gas stream.
  • the hot gas In addition, a small part of the hot gas, often unwanted, flows into various spaces in the turbine. This flow should not be the main gas flow. It is understood that the gas may also be a gas mixture.
  • the platform is characterized in that there is at least one hole on the projection through which cooling fluid flowing from a coolant supply of the blade can exit, the hole being inclined so that film cooling on the projection can be effected.
  • the formation of a film cooling brings a decisive advantage. This can be achieved with less cooling air cooling. It is important that a film is formed with cooling air, which prevents hot gas flows to the platform. Often, the film cooling is not the drain the heat through cooling air in the foreground, but the prevention of heat supply by inflowing hot gas.
  • cooling air in a turbine is added to the hot gas that is to be expanded to obtain mechanical work. This admixture lowers the recoverable mechanical work and thus the efficiency of the turbine. Therefore, it is advantageous to achieve the required cooling with as little cooling air.
  • the hole is inclined.
  • the inclination causes the cooling air exiting the hole to flow along the surface of the protrusion in the form of a film.
  • a film cooling can be formed.
  • the induced flow leads from the projection to the plane. This is achieved by the proper inclination and arrangement of the hole.
  • the film cooling may also extend to the blade leading edge.
  • the protrusion has a first region leading away from the plane at an angle to the plane, the first region merging into a second region that is substantially parallel to the plane or at an angle less than 45 ° to the plane.
  • the projection forms in this embodiment, as it were a step below the plane.
  • the first region leaves at an angle to the plane.
  • the first region can lead away from the plane largely perpendicular to the plane. But there are also smaller angles possible. In general, the angle is not less than 45 °. As far as the first area leads away from the plane largely perpendicular to the plane, it is clear that it does not have to be an exact right angle.
  • first region and / or the second region and / or the transition region extend at least partially round from the first region into the second region, so that the angle to the plane changes along the respective regions. Such round areas often prevent unwanted flow at edges.
  • the hole is arranged in the transition region from the first region to the second region. Through a hole there, the film cooling can be effectively effected and thus the otherwise to be feared in this area flow to the platform by hot gas can be prevented.
  • a plurality of holes are arranged. Through a plurality of holes, a sufficient volume flow of cooling air can be achieved without requiring a particularly high velocity of the outflowing cooling air. This favors that the cooling air remains on the surface of the projection, so there forms a cooling air film for the film cooling.
  • cooling air can escape through a plurality of holes at different points, so that cooling air can be provided in a geometrically larger area.
  • the plurality of holes are arranged in a line next to each other. It is particularly conceivable to arrange a plurality of holes next to one another in the line in which the above-described first region of the projection merges into the second region. When installed in the turbomachine, this results in an arrangement of a plurality of holes along a circumferential line.
  • a blade side space of the blade that is open on one side and that lies radially inside the plane of the platform is part of the coolant supply.
  • Such a vane side space is often easy to accommodate and allows efficient coolant supply, especially for the present cooling.
  • turbomachine containing blades with a platform described above.
  • the projection projects in each case from one platform into the vane end of an axially adjacent vane.
  • the exact configuration and the advantages of such a configuration are already shown above in the explanation of the platform as such.
  • Fig. 1 shows a section of a turbomachine designed as a turbomachine in a section in a plane parallel to the axis of the gas turbine.
  • the arrow shows the flow direction of the main gas flow of the gas to be expanded and follows the axial direction. Perpendicular to this is the radial direction.
  • first vane 1 which ends in the axial direction with a vane trailing edge 2. After a gap 3 is followed by a blade 4, bounded by a blade leading edge 5 and a blade trailing edge 6. After a further space 7 follows a leading edge of the guide blade 8 of the guide vane.
  • a guide vane closure 10 is arranged at the radially inner end of the guide vane 1.
  • a platform 12 is arranged at the radially inner end of the blade 4.
  • the platform 12 ends at its radially outer end with the plane 13 from which the blade 4 protrudes.
  • the projection 14 protrudes to the adjacent Leitschaufelab gleich 10th
  • a coolant channel 15 which leads to a hole 16.
  • the hole 16 lies in a transition region from a first region 17 lying largely perpendicular to the plane 13 into a second region 18 lying substantially parallel to the plane 13.
  • the hole 16 is inclined so that the exiting cooling air from the hole 16 on the projection 14 along, more specifically, along the first region 17, flows to the plane 13 to form a film. Thus, it forms a film cooling, which prevents, in particular, that hot gas flows to the platform 12.
  • the cooling channel 15 opens into further cooling channels which extend parallel to the plane 13 of the platform. These can be made by a lateral bore and then sealed, such as by welding. Thus, extending from a radially within the platform 12 lying blade side space 19 to the projection 14, a channel 20. This can be made later by drilling. At a junction 21, the cooling channel 15 branches off.
  • the channel 20 is provided on the projection side with a weld closure 22 in order to ensure that cooling air flows at the branch 21 into the cooling channel 15 and does not continue to flow in the channel 20.
  • FIG. 2 The perspective view of Fig. 2 results from a view as it were radially from outside to inside.
  • Fig. 2 A number of details are presented which are not relevant to the present invention and therefore will not be described.
  • the vane 4 is shown cut off. It can be seen in Fig. 2 on the left the blade leading edge 5 and on the right the blade trailing edge 6. The blade 4 protrudes from the platform 12 out. Due to the many details, level 13 may not be so obvious.
  • Fig.2 Important in the presentation of Fig.2 is that several holes 16 can be seen.
  • the holes 16 are arranged side by side in the circumferential direction. Starting from the holes 16, a cooling air film forms, which flows from the projection 14 to the plane 13 and there to the blade leading edge 5.
  • a bore is first made, which is then closed again in particular by welding, so that the cooling air does not escape undesirably, but flows through the coolant channel 15 and the holes 16.
EP16165557.6A 2016-04-15 2016-04-15 Plateforme d'une aube comprenant des trous de refroidissement a film et turbomachine associée Withdrawn EP3232000A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP16165557.6A EP3232000A1 (fr) 2016-04-15 2016-04-15 Plateforme d'une aube comprenant des trous de refroidissement a film et turbomachine associée

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16165557.6A EP3232000A1 (fr) 2016-04-15 2016-04-15 Plateforme d'une aube comprenant des trous de refroidissement a film et turbomachine associée

Publications (1)

Publication Number Publication Date
EP3232000A1 true EP3232000A1 (fr) 2017-10-18

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP16165557.6A Withdrawn EP3232000A1 (fr) 2016-04-15 2016-04-15 Plateforme d'une aube comprenant des trous de refroidissement a film et turbomachine associée

Country Status (1)

Country Link
EP (1) EP3232000A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021150418A1 (fr) * 2020-01-22 2021-07-29 General Electric Company Pale de rotor de turbine avec joints d'étanchéité d'aile d'ange avec passage de transfert de fluide de refroidissement entre des parties d'espace de roue adjacentes par fabrication additive
EP3854993A3 (fr) * 2020-01-22 2021-08-18 General Electric Company Pieds d'aube rotorique de turbine
US11220916B2 (en) 2020-01-22 2022-01-11 General Electric Company Turbine rotor blade with platform with non-linear cooling passages by additive manufacture

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1205634A2 (fr) 2000-11-03 2002-05-15 General Electric Company Refroidissement d'une aube de turbine à gaz
EP1795707A2 (fr) 2005-12-08 2007-06-13 The General Electric Company Raccordement pour bord d'attaque d'aube de turbine à gaz
US20090023660A1 (en) 1999-09-27 2009-01-22 Chugai Seiyaku Kabushiki Kaisha, a corporation of Japan Novel Hemopoietin Receptor Protein, NR12
US20100054954A1 (en) * 2008-09-04 2010-03-04 General Electric Company Turbine bucket for a turbomachine and method of reducing bow wave effects at a turbine bucket
EP2388435A2 (fr) 2010-05-19 2011-11-23 General Electric Company Aube rotorique de turbine à plate-forme refroidie
EP2423435A1 (fr) 2010-08-30 2012-02-29 Siemens Aktiengesellschaft Aube de turbomachine
WO2013165503A2 (fr) * 2012-02-15 2013-11-07 United Technologies Corporation Trou de refroidissement avec attachement à écoulement amélioré
US20140154063A1 (en) * 2012-12-05 2014-06-05 General Electric Company Airfoil and a method for cooling an airfoil platform
US20150056073A1 (en) * 2013-08-21 2015-02-26 General Electric Company Method and system for cooling rotor blade angelwings

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090023660A1 (en) 1999-09-27 2009-01-22 Chugai Seiyaku Kabushiki Kaisha, a corporation of Japan Novel Hemopoietin Receptor Protein, NR12
EP1205634A2 (fr) 2000-11-03 2002-05-15 General Electric Company Refroidissement d'une aube de turbine à gaz
EP1795707A2 (fr) 2005-12-08 2007-06-13 The General Electric Company Raccordement pour bord d'attaque d'aube de turbine à gaz
US20100054954A1 (en) * 2008-09-04 2010-03-04 General Electric Company Turbine bucket for a turbomachine and method of reducing bow wave effects at a turbine bucket
EP2388435A2 (fr) 2010-05-19 2011-11-23 General Electric Company Aube rotorique de turbine à plate-forme refroidie
EP2423435A1 (fr) 2010-08-30 2012-02-29 Siemens Aktiengesellschaft Aube de turbomachine
WO2013165503A2 (fr) * 2012-02-15 2013-11-07 United Technologies Corporation Trou de refroidissement avec attachement à écoulement amélioré
US20140154063A1 (en) * 2012-12-05 2014-06-05 General Electric Company Airfoil and a method for cooling an airfoil platform
US20150056073A1 (en) * 2013-08-21 2015-02-26 General Electric Company Method and system for cooling rotor blade angelwings

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021150418A1 (fr) * 2020-01-22 2021-07-29 General Electric Company Pale de rotor de turbine avec joints d'étanchéité d'aile d'ange avec passage de transfert de fluide de refroidissement entre des parties d'espace de roue adjacentes par fabrication additive
EP3854993A3 (fr) * 2020-01-22 2021-08-18 General Electric Company Pieds d'aube rotorique de turbine
US11220916B2 (en) 2020-01-22 2022-01-11 General Electric Company Turbine rotor blade with platform with non-linear cooling passages by additive manufacture
US11248471B2 (en) 2020-01-22 2022-02-15 General Electric Company Turbine rotor blade with angel wing with coolant transfer passage between adjacent wheel space portions by additive manufacture
US11492908B2 (en) 2020-01-22 2022-11-08 General Electric Company Turbine rotor blade root with hollow mount with lattice support structure by additive manufacture

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