JP5879022B2 - タービン翼冷却回路 - Google Patents
タービン翼冷却回路 Download PDFInfo
- Publication number
- JP5879022B2 JP5879022B2 JP2009285846A JP2009285846A JP5879022B2 JP 5879022 B2 JP5879022 B2 JP 5879022B2 JP 2009285846 A JP2009285846 A JP 2009285846A JP 2009285846 A JP2009285846 A JP 2009285846A JP 5879022 B2 JP5879022 B2 JP 5879022B2
- Authority
- JP
- Japan
- Prior art keywords
- insert
- trailing edge
- chamber
- airfoil
- pin array
- 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.)
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- 238000001816 cooling Methods 0.000 title claims description 80
- 239000012528 membrane Substances 0.000 claims description 11
- 238000011144 upstream manufacturing Methods 0.000 claims description 8
- 238000012546 transfer Methods 0.000 description 20
- 238000000034 method Methods 0.000 description 11
- 238000005266 casting Methods 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 230000035882 stress Effects 0.000 description 5
- 230000004323 axial length Effects 0.000 description 3
- 230000007423 decrease Effects 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000005192 partition Methods 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000003491 array Methods 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 239000002803 fossil fuel Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000012552 review Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
-
- 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
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
112 前縁
114 加圧側
116 吸引側
118 後縁
119 スロート
120 前縁チャンバ
122 後縁チャンバ
124 中間仕切り
126 前縁インサート
128 後縁インサート
133 外壁
146 冷却ピン
152 ピンアレイ部分
156 先細出口
Claims (9)
- 冷却空気を受け入れるチャンバ(122)を規定する外壁(133)を有するほぼ中空のエーロフォイル(110)を有するタービン翼であって、
前記エーロフォイル(110)が、上流側方向に位置する前縁(112)と、下流側方向に位置する後縁(118)と、凸形の吸引側(116)と、凹形の加圧側(114)と、前記チャンバ(122)の内部に配置されたインサート(128)であって前記チャンバ(122)に流入した前記冷却空気の少なくとも一部を最初に受け入れ且つ複数のインサート開口(130)を介して前記冷却空気を送り出すことによって前記外壁(133)の内面を冷却するように構成されたインサート(128)とを具備しており、
前記インサート(128)が、前記チャンバ(122)の前記外壁(133)の輪郭形状とほぼ同様の形状を有するが、前記外壁(133)から離間して配置される構成を更に含んでおり、
前記冷却空気の一部は、前記外壁(133)を貫通して形成された複数の膜冷却開口(132)を介して前記エーロフォイル(110)から排出され、
前記チャンバ(122)及び前記インサート(128)が、前記後縁(118)に向かって収束して、前記インサート(128)が下流側終端点で終端し且つ前記チャンバ(122)がピンアレイ部分(152)で終端していて、前記ピンアレイ部分(152)が、前記ピンアレイ部分(152)を規定する対向する壁と一体である複数の冷却ピン(146)が架け渡されている流路からなり、前記インサート(128)の下流側終端点と前記ピンアレイ部分(152)の上流側開始点との間の軸方向距離である第1の距離が存在し、
前記ピンアレイ部分(152)が、その下流端に、複数の後縁冷却開口(144)への入口を規定する複数の開口を有していて、前記複数の後縁冷却開口(144)が、前記ピンアレイ部分(152)から前記冷却空気の一部が前記エーロフォイル(110)から排出される際に通過する出口が規定された前記エーロフォイル(110)の後縁(118)まで延出しており、
前記チャンバ(122)、前記インサート(128)及び前記ピンアレイ部分(152)が、前記チャンバ(122)の広い幅から前記ピンアレイ部分(152)の狭い幅まで滑らかに大きく湾曲する先細出口(156)を設けることによって、前記第1の距離が短縮されるように構成されている、タービン翼。 - 前記タービン翼が動翼である、請求項1記載のタービン翼。
- 下流側に向かう方向に沿って見た場合、前記先細出口(156)の形状は、流路を急速に狭める凸形湾曲へと続く凹形湾曲を有する、請求項1又は請求項2記載のタービン翼。
- 前記ピンアレイ部分(152)の前記ピン(146)は複数の列を成すように構成される、請求項1乃至請求項3のいずれか1項記載のタービン翼。
- 前記複数の列の各列に含まれる前記ピン(146)は、それぞれ隣接する列のピン(146)に対して半径方向に位置がずれている、請求項4記載のタービン翼。
- 前記チャンバ(122)が、仕切り(124)により分離された前縁チャンバ(120)及び後縁チャンバ(122)を具備する、請求項1乃至請求項5のいずれか1項記載のタービン翼。
- 前記外壁(133)を貫通する前記膜冷却開口(132)のすべてが、隣接して取り付けられた2つのエーロフォイル(110)の間の最小流量領域を含むスロート(119)の上流側の場所に配置される、請求項1乃至請求項6のいずれか1項記載のタービン翼。
- 前記第1の距離を短縮する前記チャンバ(122)、前記インサート(128)及び前記ピンアレイ部分(152)の構成が、組み立て中に前記エーロフォイル(110)に差し込み可能である形状を維持しつつ前記インサート(128)が前記後縁(118)に向かって最大距離で延出するように前記インサート(128)の前記後縁が構成されることを含む、請求項1記載のタービン翼。
- 前記第1の距離を短縮する前記チャンバ(122)、前記インサート(128)及び前記ピンアレイ部分(152)の構成が、前記インサート(128)の最小曲率、前記外壁(133)の最小壁厚さ及び最小後縁流路厚さが規定されている場合に前記インサート(128)が前記後縁(118)に向かって最大距離で延出するように前記インサート(128)の前記後縁が構成されることを含む、請求項1記載のタービン翼。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/346,278 US8231329B2 (en) | 2008-12-30 | 2008-12-30 | Turbine blade cooling with a hollow airfoil configured to minimize a distance between a pin array section and the trailing edge of the air foil |
US12/346,278 | 2008-12-30 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2010156322A JP2010156322A (ja) | 2010-07-15 |
JP5879022B2 true JP5879022B2 (ja) | 2016-03-08 |
Family
ID=42077831
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2009285846A Active JP5879022B2 (ja) | 2008-12-30 | 2009-12-17 | タービン翼冷却回路 |
Country Status (4)
Country | Link |
---|---|
US (1) | US8231329B2 (ja) |
EP (1) | EP2204538B1 (ja) |
JP (1) | JP5879022B2 (ja) |
CN (1) | CN101769170B (ja) |
Families Citing this family (39)
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US8152468B2 (en) * | 2009-03-13 | 2012-04-10 | United Technologies Corporation | Divoted airfoil baffle having aimed cooling holes |
US9033652B2 (en) | 2011-09-30 | 2015-05-19 | General Electric Company | Method and apparatus for cooling gas turbine rotor blades |
EP2628901A1 (en) * | 2012-02-15 | 2013-08-21 | Siemens Aktiengesellschaft | Turbine blade with impingement cooling |
EP2682565B8 (en) | 2012-07-02 | 2016-09-21 | General Electric Technology GmbH | Cooled blade for a gas turbine |
US20140075947A1 (en) * | 2012-09-18 | 2014-03-20 | United Technologies Corporation | Gas turbine engine component cooling circuit |
US9995148B2 (en) | 2012-10-04 | 2018-06-12 | General Electric Company | Method and apparatus for cooling gas turbine and rotor blades |
EP2754856A1 (en) * | 2013-01-09 | 2014-07-16 | Siemens Aktiengesellschaft | Blade for a turbomachine |
GB201311333D0 (en) | 2013-06-26 | 2013-08-14 | Rolls Royce Plc | Component for use in releasing a flow of material into an environment subject to periodic fluctuations in pressure |
US9581028B1 (en) | 2014-02-24 | 2017-02-28 | Florida Turbine Technologies, Inc. | Small turbine stator vane with impingement cooling insert |
EP2921649B1 (en) | 2014-03-19 | 2021-04-28 | Ansaldo Energia IP UK Limited | Airfoil portion of a rotor blade or guide vane of a turbo-machine |
US9771816B2 (en) | 2014-05-07 | 2017-09-26 | General Electric Company | Blade cooling circuit feed duct, exhaust duct, and related cooling structure |
US9638045B2 (en) | 2014-05-28 | 2017-05-02 | General Electric Company | Cooling structure for stationary blade |
US10502066B2 (en) | 2015-05-08 | 2019-12-10 | United Technologies Corporation | Turbine engine component including an axially aligned skin core passage interrupted by a pedestal |
US10323524B2 (en) * | 2015-05-08 | 2019-06-18 | United Technologies Corporation | Axial skin core cooling passage for a turbine engine component |
US9822653B2 (en) | 2015-07-16 | 2017-11-21 | General Electric Company | Cooling structure for stationary blade |
US9909436B2 (en) | 2015-07-16 | 2018-03-06 | General Electric Company | Cooling structure for stationary blade |
US10344598B2 (en) * | 2015-12-03 | 2019-07-09 | General Electric Company | Trailing edge cooling for a turbine blade |
EP3192970A1 (en) * | 2016-01-15 | 2017-07-19 | General Electric Technology GmbH | Gas turbine blade and manufacturing method |
US10352177B2 (en) | 2016-02-16 | 2019-07-16 | General Electric Company | Airfoil having impingement openings |
US10655477B2 (en) * | 2016-07-26 | 2020-05-19 | General Electric Company | Turbine components and method for forming turbine components |
US10443397B2 (en) * | 2016-08-12 | 2019-10-15 | General Electric Company | Impingement system for an airfoil |
US10408062B2 (en) * | 2016-08-12 | 2019-09-10 | General Electric Company | Impingement system for an airfoil |
US10436048B2 (en) * | 2016-08-12 | 2019-10-08 | General Electric Comapny | Systems for removing heat from turbine components |
US10364685B2 (en) * | 2016-08-12 | 2019-07-30 | Gneral Electric Company | Impingement system for an airfoil |
FR3057906B1 (fr) * | 2016-10-20 | 2019-03-15 | Safran Aircraft Engines | Aube de turbomachine a refroidissement optimise |
US10577942B2 (en) * | 2016-11-17 | 2020-03-03 | General Electric Company | Double impingement slot cap assembly |
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US10731474B2 (en) * | 2018-03-02 | 2020-08-04 | Raytheon Technologies Corporation | Airfoil with varying wall thickness |
US10753210B2 (en) * | 2018-05-02 | 2020-08-25 | Raytheon Technologies Corporation | Airfoil having improved cooling scheme |
CN110792635B (zh) * | 2018-08-02 | 2021-07-23 | 宁波方太厨具有限公司 | 一种散热风机及安装有该风机的厨房空气调节系统 |
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2008
- 2008-12-30 US US12/346,278 patent/US8231329B2/en active Active
-
2009
- 2009-12-11 EP EP09178851.3A patent/EP2204538B1/en active Active
- 2009-12-17 JP JP2009285846A patent/JP5879022B2/ja active Active
- 2009-12-30 CN CN200910113668.6A patent/CN101769170B/zh active Active
Also Published As
Publication number | Publication date |
---|---|
EP2204538B1 (en) | 2019-06-05 |
CN101769170A (zh) | 2010-07-07 |
CN101769170B (zh) | 2014-05-28 |
EP2204538A3 (en) | 2014-10-08 |
US8231329B2 (en) | 2012-07-31 |
US20100166564A1 (en) | 2010-07-01 |
JP2010156322A (ja) | 2010-07-15 |
EP2204538A2 (en) | 2010-07-07 |
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