EP2882940A1 - Composant et procédé de refroidissement d'un composant - Google Patents
Composant et procédé de refroidissement d'un composantInfo
- Publication number
- EP2882940A1 EP2882940A1 EP13730991.0A EP13730991A EP2882940A1 EP 2882940 A1 EP2882940 A1 EP 2882940A1 EP 13730991 A EP13730991 A EP 13730991A EP 2882940 A1 EP2882940 A1 EP 2882940A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- component
- adjacent
- diffusion
- zone
- trailing edge
- 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- Withdrawn
Links
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
-
- 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
- F01D5/186—Film cooling
-
- 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
-
- 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
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
-
- 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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
-
- 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
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
-
- 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 present invention relates generally to turbines. More specifically, to a component and a method of cooling a component in turbine.
- One strategy for alleviating thermal stresses is through cooling the airfoils such that the temperatures experienced by the airfoils are Sower than that of the hot-gas path. Effective cooling may, for example, allow the airfoils to withstand higher firing temperatures, withstand greater mechanical stresses at high operating temperatures, and/or extend the part- life of the airfoil, all of which may allow the turbine engine to be more cost-effective and efficient.
- One way to cool airfoils during operation is through the use of internal cooling passageways or circuits. Generally, this involves passing a relatively cool supply of compressed air, which may be supplied by the compressor of the turbine engine, through internal cooling circuits within the airfoils. As the compressed air passes through the airfoil, it convectively cools the airfoil, which may allow the part to withstand firing temperatures that it otherwise could not,
- the supply of compressed air is released through small holes on the surface of the airfoils. Released in this manner, the supply of air forms a thin layer or film of relatively cool air at the surface of the airfoil, which both cools and insulates the part from the higher temperatures that surround it.
- This type of cooling which is commonly referred to as “film cooling,” however, comes at an expense.
- film cooling comes at an expense.
- the release of the compressed air in this manner over the surface of the airfoil lowers the aero-efficiency of the engine. As a result, there is an ongoing need for improved cooling strategies for turbine airfoils.
- a component may include a leading edge, a trailing edge, at least one cavity between the leading edge and the trailing edge and at least one diffusion member adjacent to the cavity.
- the diffusion member may include an inlet adjacent to the cavity, a metering zone adjacent to the inlet, a diffusion zone adjacent to the metering zone, and an outlet adjacent the diffusion zone and adjacent the trailing edge.
- the diffusion member may provide up to about 70% reduction in flow and uniform cooling of the trailing edge of the component.
- a method of cooling a component may include providing the component.
- the component may include a leading edge, a trailing edge, at least one cavity between the leading edge and the trailing edge and at least one diffusion member adjacent to the cavity.
- the diffusion member may include an inlet adjacent to the cavity, a metering zone adjacent to the inlet, a diffusion zone adjacent to the metering zone, and an outlet adjacent the diffusion zone and adjacent the trailing edge.
- the diffusion member may provide up to about 70% reduction in flow and uniform cooling of the trailing edge of the component.
- the method may include circulating cooling air in the at least one cavity through the diffusion member. The heat from the component may be removed through the diffusion zone.
- FIG. 1 is a perspective schematic of a component of the present disclosure.
- FIG. 2 is a blown-up view of FIG. 1 of the diffusion zone of the present disclosure.
- FIG. 3 section view of FIG. 1 taken along line 3-3 of the present disclosure.
- FIG. 4 is a blown-up view of the diffusion zone of FIG. 3 of the present disclosure.
- FIG. 5 is an alternative embodiment of the diffusion zone of FIG. 3 of the present disclosure.
- FIG. 6 is an alternative embodiment of the diffusion zone of the present disclosure.
- One advantage of an embodiment of the present disclosure includes reducing parasitic flows from a turbine. Another advantage of an embodiment of the present disclosure includes reducing the discharge velocity of the nozzle trailing edge cooling slots. Yet another advantage of the present disclosure is increased engine efficiency.
- a component including a leading edge, a trailing edge, at least one cavity between the leading edge and the trailing edge, and at least one diffusion member adjacent to the cavity.
- Component may generally be a hot gas flow path component and may include turbine components, such as, but not limited to, nozzles, blades and shrouds.
- the diffusion member may provide up to about 70% reduction in flow and uniform cooling of the trailing edge of the component, in one embodiment, the component may be a ceramic matrix composite.
- the component may be a superalloy metal, such as but not limited to nickel-based superalloy, cobalt-based superalloy, or a combination thereof.
- FIG. 1 is a perspective schematic of a component 100.
- component 100 may be a nozzle.
- Component 100 may include an airfoil 102.
- Airfoil 1 02 may be a member between the inner and outer turbine flow path with purpose to change the flow gas path direction. Airfoil may include a leading edge 1 10, a trailing edge 1 12, and a body 104 between leading edge 1 10 and trailing edge 1 12.
- component 100 may include at least one cavity 200, 310, 320 between leading edge 1 10 and trailing edge 1 12.
- Component 100 may include at least one diffusion member 130 adjacent to the at least one cavity.
- diffusion member may include an inlet adjacent to the cavity, a metering zone adjacent to the inlet, a diffusion zone adjacent to the metering zone, and an outlet adjacent the diffusion zone and adjacent the trailing edge.
- diffusion member 130 may include an inlet 210 adjacent to cavity 200.
- Diffusion member 130 may include a metering zone 220 adjacent to inlet 210.
- Diffusion member 130 may include a diffusion zone 230 adjacent to metering zone 220.
- Diffusion member 130 may include an outlet 240 adjacent diffusion zone 220 and adjacent trailing edge 1 12.
- Diffusion member 130 may provide up to about 70% reduction in flow and uniform cooling of trailing edge S 12 of component 100. Velocity of flow at outlet 240 may be significantly reduced.
- Diffusion member 130 may expand the cross section area from inlet 210 to outlet 240.
- flow expansion may be a process in which the mass flux is reduced with increasing through-flow area, or a device that enables said process, such as the diffusion member 120.
- flow metering may be a process or device that controls the quantity of flow traversing the member containing the metering process or device.
- inlet 210 may be the location that flow enters trailing edge 1 12 cooling scheme from aft cavity 200 (see FIG. 3). Inlet 210 may be typically short in length with the ratio of the length to hydraulic diameter being less than about 5. Inlet 210 may have unique geometric characteristics intended to reduce its metering characteristics.
- Metering zone 220 may be primarily a controlled geometry feature the size of which has the most significant impact on the flow rate passing tl rough trailing edge 1 12 cooling scheme.
- Metering zone 220 may have a secondary geometry feature that causes or is intended to cause a reduction in the flow rate. Secondary metering may have a non-negligible impact on flow rate but may not be the flow controlling feature.
- Diffusion zone 230 or expansion region may be a region with through-flow area increase of about 150% to about 500%, between the metering zone 220 and outlet 240.
- Diffusion zone 230 may include a diffusion angle 232.
- Diffusion angle 232 may be any angle that provides the desired expansion of flow.
- Outlet 240 may be the location where flow exits internal portion of trailing edge ⁇ 12 cooling scheme.
- Outlet 240 may be characterized by film coverage and in the event outlet 240 bisects the trailing edge 1 12 with no film coverage zone, then outlet 240 may have an open-to-sohd ratio in the range of about 25% to about 100%.
- film coverage may be measured in the direction orthogonal to the flow, and is the fraction of the distance that is exposed to outlet 240.
- FIG. 3 is a sectional vie along line 3-3 of FIG. 1 and shows forward cavity 320 adjacent leading edge 110.
- Second cavity 310 may be adjacent forward cavity 320.
- Aft cavity 200 may be adjacent diffusion member 130.
- Diffusion member 130 may be adjacent external portion 350.
- External portion 350 may be the distance between outlet 240 of diffusion member 130 and airfoil closeout, having a ratio of length (L) to hydraulic diameter (D) in the range of about zero to about twelve.
- L length
- D hydraulic diameter
- the film coverage may be in the range of about 33% to 100%.
- the outlet 240 may have "open" coverage in the range of about 33% to 100%.
- FIG. 4 illustrates a schematic biow-up of FIG. 3 higlilighting the diffusion member 130.
- Inlet 210 may be adjacent to aft cavity 200
- Metering zone 220 may be adjacent inlet 210.
- Diffusion zone 230 may be adjacent metering zone 220.
- Outlet 240 may be adjacent diffusion zone and external portion 350 of airfoil 102 trailing edge 1 12.
- outlet 240 may exit at base of trailing edge 112, having no breakout length.
- a diffusion member may include two or more diffusion zones.
- diffusion member 130 may include inlet 210 adjacent to aft cavity 220 of component 100.
- Inlet 210 may be adjacent to metering zone 220.
- There may be two or more diffusion zones 230 adjacent to metering zone 220.
- Each diffusion zone 230 may provide the desired expansion and decrease in flow.
- Each diffusion zone 230 may include an outlet 240 adjacent to trailing edge 1 12.
- Diffusion member 130 may be formed in component 100 using any suitable technologies, such as, but not limited to, lasers, or electrical discharge machining (EDM).
- EDM electrical discharge machining
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
L'invention concerne un composant (100) et un procédé de refroidissement d'un composant (100). Le composant (100) comprend un bord avant (110), un bord arrière (112), au moins une cavité (200) entre le bord avant (110) et le bord arrière (112), au moins un élément de diffusion (130) au voisinage de la cavité (200). L'élément de diffusion (130) comprend une entrée (210) au voisinage de la cavité (200), une zone de dosage (220) au voisinage de l'entrée (210), une zone de diffusion (230) au voisinage de la zone de dosage (220), et une sortie (240) au voisinage de la zone de diffusion (230) et au voisinage du bord arrière (112). L'élément de diffusion (130) fournit jusqu'à environ 70 % de réduction d'écoulement et un refroidissement uniforme du bord arrière du composant (100).
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201261666813P | 2012-06-30 | 2012-06-30 | |
US13/826,976 US20140003937A1 (en) | 2012-06-30 | 2013-03-14 | Component and a method of cooling a component |
PCT/US2013/044415 WO2014004014A1 (fr) | 2012-06-30 | 2013-06-06 | Composant et procédé de refroidissement d'un composant |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2882940A1 true EP2882940A1 (fr) | 2015-06-17 |
Family
ID=49778353
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13730991.0A Withdrawn EP2882940A1 (fr) | 2012-06-30 | 2013-06-06 | Composant et procédé de refroidissement d'un composant |
Country Status (7)
Country | Link |
---|---|
US (1) | US20140003937A1 (fr) |
EP (1) | EP2882940A1 (fr) |
JP (1) | JP2015526629A (fr) |
CN (1) | CN104379874A (fr) |
BR (1) | BR112015000077A2 (fr) |
CA (1) | CA2877330A1 (fr) |
WO (1) | WO2014004014A1 (fr) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10301954B2 (en) * | 2016-01-08 | 2019-05-28 | General Electric Company | Turbine airfoil trailing edge cooling passage |
US10352176B2 (en) * | 2016-10-26 | 2019-07-16 | General Electric Company | Cooling circuits for a multi-wall blade |
US10450950B2 (en) * | 2016-10-26 | 2019-10-22 | General Electric Company | Turbomachine blade with trailing edge cooling circuit |
US10309227B2 (en) * | 2016-10-26 | 2019-06-04 | General Electric Company | Multi-turn cooling circuits for turbine blades |
US11814965B2 (en) | 2021-11-10 | 2023-11-14 | General Electric Company | Turbomachine blade trailing edge cooling circuit with turn passage having set of obstructions |
US20230193764A1 (en) * | 2021-12-17 | 2023-06-22 | Raytheon Technologies Corporation | Gas turbine engine component with manifold cavity and metering inlet orifices |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4684323A (en) * | 1985-12-23 | 1987-08-04 | United Technologies Corporation | Film cooling passages with curved corners |
JP3302370B2 (ja) * | 1995-04-11 | 2002-07-15 | ユナイテッド・テクノロジーズ・コーポレーション | 薄膜冷却スロットを備えたタービンブレードの外部エアシール |
US6287075B1 (en) * | 1997-10-22 | 2001-09-11 | General Electric Company | Spanwise fan diffusion hole airfoil |
US6176678B1 (en) * | 1998-11-06 | 2001-01-23 | General Electric Company | Apparatus and methods for turbine blade cooling |
EP1167690A1 (fr) * | 2000-06-21 | 2002-01-02 | Siemens Aktiengesellschaft | Refroidissement du bord de fuite d'une aube de turbine à gaz |
US6969230B2 (en) * | 2002-12-17 | 2005-11-29 | General Electric Company | Venturi outlet turbine airfoil |
US7300252B2 (en) * | 2004-10-04 | 2007-11-27 | Alstom Technology Ltd | Gas turbine airfoil leading edge cooling construction |
US7374401B2 (en) * | 2005-03-01 | 2008-05-20 | General Electric Company | Bell-shaped fan cooling holes for turbine airfoil |
US7686578B2 (en) * | 2006-08-21 | 2010-03-30 | General Electric Company | Conformal tip baffle airfoil |
US7549844B2 (en) * | 2006-08-24 | 2009-06-23 | Siemens Energy, Inc. | Turbine airfoil cooling system with bifurcated and recessed trailing edge exhaust channels |
US7762775B1 (en) * | 2007-05-31 | 2010-07-27 | Florida Turbine Technologies, Inc. | Turbine airfoil with cooled thin trailing edge |
US8092177B2 (en) * | 2008-09-16 | 2012-01-10 | Siemens Energy, Inc. | Turbine airfoil cooling system with diffusion film cooling hole having flow restriction rib |
US8096771B2 (en) * | 2008-09-25 | 2012-01-17 | Siemens Energy, Inc. | Trailing edge cooling slot configuration for a turbine airfoil |
US8057181B1 (en) * | 2008-11-07 | 2011-11-15 | Florida Turbine Technologies, Inc. | Multiple expansion film cooling hole for turbine airfoil |
US8319146B2 (en) * | 2009-05-05 | 2012-11-27 | General Electric Company | Method and apparatus for laser cutting a trench |
US20110268583A1 (en) * | 2010-04-30 | 2011-11-03 | General Electric Company | Airfoil trailing edge and method of manufacturing the same |
US9416971B2 (en) * | 2012-02-15 | 2016-08-16 | United Technologies Corporation | Multiple diffusing cooling hole |
-
2013
- 2013-03-14 US US13/826,976 patent/US20140003937A1/en not_active Abandoned
- 2013-06-06 JP JP2015520221A patent/JP2015526629A/ja active Pending
- 2013-06-06 CN CN201380035010.2A patent/CN104379874A/zh active Pending
- 2013-06-06 WO PCT/US2013/044415 patent/WO2014004014A1/fr active Application Filing
- 2013-06-06 BR BR112015000077A patent/BR112015000077A2/pt not_active IP Right Cessation
- 2013-06-06 EP EP13730991.0A patent/EP2882940A1/fr not_active Withdrawn
- 2013-06-06 CA CA2877330A patent/CA2877330A1/fr not_active Abandoned
Non-Patent Citations (2)
Title |
---|
None * |
See also references of WO2014004014A1 * |
Also Published As
Publication number | Publication date |
---|---|
CN104379874A (zh) | 2015-02-25 |
JP2015526629A (ja) | 2015-09-10 |
CA2877330A1 (fr) | 2014-01-03 |
US20140003937A1 (en) | 2014-01-02 |
BR112015000077A2 (pt) | 2017-10-10 |
WO2014004014A1 (fr) | 2014-01-03 |
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