EP2894301A1 - Segment de bouclier thermique de stator - Google Patents
Segment de bouclier thermique de stator Download PDFInfo
- Publication number
- EP2894301A1 EP2894301A1 EP14151020.6A EP14151020A EP2894301A1 EP 2894301 A1 EP2894301 A1 EP 2894301A1 EP 14151020 A EP14151020 A EP 14151020A EP 2894301 A1 EP2894301 A1 EP 2894301A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- serpentine
- heat shield
- stator heat
- shield segment
- channel
- 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- Withdrawn
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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
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
Definitions
- the present invention relates to cooling for gas turbine, in particular, to a stator heat shield segment for a gas turbine.
- stator heat shields are situated on a stator and/or on a housing of a gas turbine. They are usually mounted on a guide vane carrier and form a radial border for a hot gas path of the gas turbine in the area of the rotor blades of a rotor of the gas turbine.
- a plurality of such stator heat shields is arranged adjacent to one another in the circumferential direction with regard to an axis of rotation of the rotor, thereby forming a closed ring of individual stator heat shields.
- the individual stator heat shields here form ring segments.
- the stator heat shields protect the housing and/or the guide vane carriers from exposure to the hot gas of the gas turbine.
- stator heat shields The outside of the stator heat shields is exposed to the hot gas, while the inside of the respective stator heat shield facing away from the hot gas path is exposed to a suitable cooling air to cool the respective stator heat shield. Due to this cooling, the lifetime of the stator heat shields can be increased. Fundamentally, however, there is a need for increasing the lifetime of such stator heat shields further. Cooling of a stator heat shield(SHS), particularly of first stage is a very challenge task. Cooling effectiveness is limited to convective cooling scheme, since film cooling of hot gas exposed surface is not applicable at area where the rotating blade passes the SHS. This is for two reasons.
- a component of a gas turbine engine is provided in US20120251295 A1 .
- the component includes an external wall which, in use, is exposed on one surface thereof to working gas flowing through the engine.
- the component further includes effusion cooling holes formed in the external wall. In use, cooling air blows through the cooling holes to form a cooling film on the surface of the external wall exposed to the working gas.
- the component further includes an air inlet arrangement which receives the cooling air for distribution to the cooling holes.
- the component further includes a plurality of metering feeds and a plurality of supply plena. The metering feeds meter the cooling air from the air inlet arrangement to respective of the supply plena, which in turn supply the metered cooling air to respective portions of the cooling holes.
- a shroud section for a gas turbine engine is proposed in US6139257 A .
- high pressure cooling air is directed in metered flow to baffle plenums and thence through baffle perforations to impingement cool the rails and back surfaces of the shroud.
- Impingement cooling air then flows through elongated, convection cooling passages in the shroud sections and exits to flow along the shroud front surface with the main gas stream to provide film cooling.
- the aft rail of the shroud sections is provided with one or more cooling holes to impingement cool the annular retaining ring or C-clip retaining the shroud sections on the shroud hangers. This cooling air then travels aftward on the inboard side of the C-clip to provide convection cooling of the C-clip.
- cooling air is directed at the aft corners of the shroud base to avoid overheating.
- a turbine shroud is proposed in US20050058534 A1 .
- a turbine wall includes a metal substrate having front and back surfaces.
- a thermal barrier coating is bonded atop the front surface.
- a network of flow channels is laminated between the substrate and the coating for carrying an air coolant therebetween for cooling the thermal barrier coating.
- cooling channels are separated from hot gas by thin layers of TBC and bondcoat only that strains very high level of failure risk in case of rubbing event.
- Heat shield element (HS) for a gas turbine (GT) is proposed in EP2549063A1 , which comprises an areal wall section (WS), which extends with regard to a central axis (CA) in an axial direction and a circumferential direction (CD), said wall section (WS) being defined by limiting edges of the heat shield element (HS), said wall section (WS) is of a defined thickness (TH), said thickness depending on the axial and circumferential position extending radially from an inner surface (IS) to an outer surface (OS) said inner surface (IS) is exposed to a hot gas path (HGP) and said outer surface (OS) is exposed to a coolant (CO) contained in a cavity (CV), wherein the heat shield element (HS) is provided with mounting elements (ME) suitable for mounting on a supporting structure (SP).
- cooling channels (CC) are provided through the wall of said wall section (WS) said cooling channels (CC) comprising a first section (S1) starting at the inner surface (IS), further comprising a second section (S2) extending between the inner surface (IS) and the outer surface (OS) along a length of at least three times the thickness (TH) of the wall section (WS) at that specific area of the second section and comprising a third section (S3) joining the hot gas path through the inner surface (IS) or through a limiting edge so that said cooling channels (CC) connect said cavity (CV) with the hot gas path (HGP).
- It is an object of the present invention is to provide a stator heat shield segment which may save coolant with substantial cooling effectiveness.
- a stator heat shield segment for a gas turbine comprising: an outside plate facing a hot gas path of the gas turbine; an inside plate facing away from the outside plate and exposed to cooling air; at least one serpentine cooling channel disposed between the outside plate and the inside plate, the serpentine cooling channel comprises straight portions extending parallelly with each other, bent portions connecting adjacent strait portions respectively, an inlet riser portion for introducing coolant disposed perpendicularly to the serpentine cooling channel at one end of the serpentine channel; and an outlet portion disposed at an opposite end of the serpentine channel.
- a cross section of at least a part of the straight portions is adjustable by means of additive manufacturing method.
- the additive manufacturing method is selective laser melting.
- a shape of the cross section of the serpentine channel is selected from the group consisting of square, rectangular, hexagon, trapezoid and triangle.
- grooves are disposed on a surface of the inside plate opposite to the serpentine channel in a manner that the grooves are located between the straight portions.
- a flow barrier element is disposed inside the serpentine channel.
- the flow barrier element is selected from the group consisting of plain ribs, V shaped ribs, W shaped ribs, pins, vortex generators and dimples.
- a plurality of serpentine channels are arranged in the stator heat shield segment in a manner that the plurality of serpentine channels are parallel to each other.
- Fig. 1 shows a perspective view of a stator heat shield (SHS) segment 10 according to one example embodiment of the present invention, where part of the SHS segment 10 is removed to expose the structure inside.
- the SHS segment 10 comprises a an outside plate 20 facing a hot gas path of the gas turbine; an inside plate 30(as shown in Fig.2 ) facing away from the outside plate 20 and exposed to cooling air; a serpentine cooling channel 100 disposed between the outside plate 20 and the inside plate 30.
- the serpentine cooling channel 100 comprises straight portions 104, 110 and 112 extending parallelly with each other; bent portions 106 and 108 connecting adjacent strait portions 104 and 110, and 110 and 112, respectively; a inlet riser portion 102 for introducing coolant disposed perpendicularly to the serpentine cooling channel 100 at one end of the serpentine channel 100; and an outlet portion 114 disposed at an opposite end of the serpentine channel 100.
- the inlet riser portion 102 may be structured to be a funnel shape in order to facilitate introduction of coolant, such as cooling air.
- the outlet portion 114 may be configured to angle to the straight portion 112 in order to facilitate arrangement of the serpentine channel 100 in the SHS segment 10 as shown in Fig. 3 .
- Fig. 2a-2e show part of the cross section of the SHS segment 10 according to one example embodiment of the present invention.
- the serpentine channel 100 may be configured to be a tube shape, such as a sealed tube, with certain cross section shape such as square.
- Fig.2b-2e show different cross section shape for the serpentine channels according to example embodiments of the present invention, where the cross section shape of the serpentine channel 100 may be configured to be trapezoid, rectangle, hexagon.
- grooves 40 may be disposed on a surface of the inside plate opposite to the serpentine channel 100 in a manner that the grooves 40 are located between the straight portions and extended along the straight portions 104, 110 and 112.
- the grooves 40 improve the ratio of cold to hot metal volume which in turn is beneficial for cyclic life time of the SHS segment 10.
- Fig.3 shows a plan view of another SHS segment 10 according to another example embodiment of the present invention.
- a plurality of serpentine channels 100 may be arranged in the SHS segment 10 in a manner that the plurality of serpentine channels 100 are parallel to each other.
- the cross section of at least a part of the straight portions 104, 110 and 112 may be adjusted by means of additive manufacturing method, such as selective laser melting to optimize heat transfer rates and mechanical stiffness and subsequently provide more uniform metal temperature which subsequently reduce thermal gradient.
- the straight portions of adjacent serpentine channels are narrowed to form a substantial oval shape. It should be understood by those skilled in the art that, various change can be made to the cross section of the straight portions of the serpentine channels in order to achieve desired hot gas boundary conditions.
- Fig. 4 shows another perspective view of the SHS segment 10 according to another example embodiment of the present invention.
- a flow barrier element 120 such as plain rib is disposed inside the serpentine channel 100 in order to enhance heat transfer rates.
- the plain rib is angled to a wall of the serpentine channel 100 as shown in Fig.4 .
- Fig.5a-5f show alternative structures for the flow barrier element 120, where the flow barrier element 120 may be configured to be V shaped ribs, W shaped ribs, pins, vortex generators and dimples as shown by Fig 5a to 5f respectively.
- Fig. 5a shows the flow barrier element is configured to be V shaped ribs
- Fig. 5b shows the flow barrier element is configured to be W shaped ribs
- Fig. 5c shows the flow barrier element is configured to be pins, which are disposed in middle of the serpentine channel and/or attached to the wall of the serpentine channel
- Fig. 5a-5f show alternative structures for the flow barrier element 120, where the flow barrier element 120 may be configured to be V shaped ribs, W shaped ribs, pins, vortex generators and dimples as shown by Fig 5a to 5f respectively.
- Fig. 5a shows the flow barrier element is configured to be V shaped ribs
- Fig. 5b shows the flow barrier element is configured
- FIG. 5d shows the flow barrier element is configured to be vortex generators, which are disposed in middle of the serpentine channel and/or attached to the wall of the serpentine channel
- Fig. 5e shows the flow barrier element is configured to be dimples, which are disposed in middle of the serpentine channel and/or attached to the wall of the serpentine channel.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14151020.6A EP2894301A1 (fr) | 2014-01-14 | 2014-01-14 | Segment de bouclier thermique de stator |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14151020.6A EP2894301A1 (fr) | 2014-01-14 | 2014-01-14 | Segment de bouclier thermique de stator |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2894301A1 true EP2894301A1 (fr) | 2015-07-15 |
Family
ID=49918603
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14151020.6A Withdrawn EP2894301A1 (fr) | 2014-01-14 | 2014-01-14 | Segment de bouclier thermique de stator |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP2894301A1 (fr) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3181826A1 (fr) * | 2015-12-16 | 2017-06-21 | General Electric Company | Segment d'anneau avec canaux de refroidissement de bord de fuite en forme de serpentin |
EP3306040A1 (fr) * | 2016-10-08 | 2018-04-11 | Ansaldo Energia Switzerland AG | Segment d'écran thermique de stator pour centrale électrique à turbine à gaz |
US10247106B2 (en) | 2016-06-15 | 2019-04-02 | General Electric Company | Method and system for rotating air seal with integral flexible heat shield |
US10316751B2 (en) | 2014-08-28 | 2019-06-11 | United Technologies Corporation | Shielded pass through passage in a gas turbine engine structure |
US10378380B2 (en) | 2015-12-16 | 2019-08-13 | General Electric Company | Segmented micro-channel for improved flow |
WO2019231750A1 (fr) * | 2018-05-31 | 2019-12-05 | General Electric Company | Carénage pour moteur à turbine à gaz |
US10738651B2 (en) | 2018-05-31 | 2020-08-11 | General Electric Company | Shroud for gas turbine engine |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6139257A (en) | 1998-03-23 | 2000-10-31 | General Electric Company | Shroud cooling assembly for gas turbine engine |
EP1063388A2 (fr) * | 1999-06-23 | 2000-12-27 | United Technologies Corporation | Méthode de refroidissement de paroi pour une aube de turbomachine |
US20050058534A1 (en) | 2003-09-17 | 2005-03-17 | Ching-Pang Lee | Network cooled coated wall |
US20070041827A1 (en) * | 2003-07-10 | 2007-02-22 | Snecma | Cooling circuit for gas turbine fixed ring |
US20080127652A1 (en) * | 2004-12-16 | 2008-06-05 | Heinrich Putz | Heat Shield Element |
US20100183428A1 (en) * | 2009-01-19 | 2010-07-22 | George Liang | Modular serpentine cooling systems for turbine engine components |
US20120251295A1 (en) | 2011-03-28 | 2012-10-04 | Rolls-Royce Plc | Gas turbine engine component |
EP2549063A1 (fr) | 2011-07-21 | 2013-01-23 | Siemens Aktiengesellschaft | Élément d'écran thermique pour une turbine à gaz |
US8449246B1 (en) * | 2010-12-01 | 2013-05-28 | Florida Turbine Technologies, Inc. | BOAS with micro serpentine cooling |
-
2014
- 2014-01-14 EP EP14151020.6A patent/EP2894301A1/fr not_active Withdrawn
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6139257A (en) | 1998-03-23 | 2000-10-31 | General Electric Company | Shroud cooling assembly for gas turbine engine |
EP1063388A2 (fr) * | 1999-06-23 | 2000-12-27 | United Technologies Corporation | Méthode de refroidissement de paroi pour une aube de turbomachine |
US20070041827A1 (en) * | 2003-07-10 | 2007-02-22 | Snecma | Cooling circuit for gas turbine fixed ring |
US20050058534A1 (en) | 2003-09-17 | 2005-03-17 | Ching-Pang Lee | Network cooled coated wall |
US20080127652A1 (en) * | 2004-12-16 | 2008-06-05 | Heinrich Putz | Heat Shield Element |
US20100183428A1 (en) * | 2009-01-19 | 2010-07-22 | George Liang | Modular serpentine cooling systems for turbine engine components |
US8449246B1 (en) * | 2010-12-01 | 2013-05-28 | Florida Turbine Technologies, Inc. | BOAS with micro serpentine cooling |
US20120251295A1 (en) | 2011-03-28 | 2012-10-04 | Rolls-Royce Plc | Gas turbine engine component |
EP2549063A1 (fr) | 2011-07-21 | 2013-01-23 | Siemens Aktiengesellschaft | Élément d'écran thermique pour une turbine à gaz |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10316751B2 (en) | 2014-08-28 | 2019-06-11 | United Technologies Corporation | Shielded pass through passage in a gas turbine engine structure |
EP3181826A1 (fr) * | 2015-12-16 | 2017-06-21 | General Electric Company | Segment d'anneau avec canaux de refroidissement de bord de fuite en forme de serpentin |
CN106884687A (zh) * | 2015-12-16 | 2017-06-23 | 通用电气公司 | 用于冷却涡轮护罩后缘的系统及方法 |
US10309252B2 (en) | 2015-12-16 | 2019-06-04 | General Electric Company | System and method for cooling turbine shroud trailing edge |
US10378380B2 (en) | 2015-12-16 | 2019-08-13 | General Electric Company | Segmented micro-channel for improved flow |
US10247106B2 (en) | 2016-06-15 | 2019-04-02 | General Electric Company | Method and system for rotating air seal with integral flexible heat shield |
EP3306040A1 (fr) * | 2016-10-08 | 2018-04-11 | Ansaldo Energia Switzerland AG | Segment d'écran thermique de stator pour centrale électrique à turbine à gaz |
US10508563B2 (en) | 2016-10-08 | 2019-12-17 | Ansaldo Energia Switzerland AG | Stator heat shield segment for a gas turbine power plant |
WO2019231750A1 (fr) * | 2018-05-31 | 2019-12-05 | General Electric Company | Carénage pour moteur à turbine à gaz |
US20190368377A1 (en) * | 2018-05-31 | 2019-12-05 | General Electric Company | Shroud for gas turbine engine |
US10738651B2 (en) | 2018-05-31 | 2020-08-11 | General Electric Company | Shroud for gas turbine engine |
US10989070B2 (en) | 2018-05-31 | 2021-04-27 | General Electric Company | Shroud for gas turbine engine |
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Effective date: 20160116 |