JP2010001889A - クロスフロータービンエアフォイル - Google Patents
クロスフロータービンエアフォイル Download PDFInfo
- Publication number
- JP2010001889A JP2010001889A JP2009141810A JP2009141810A JP2010001889A JP 2010001889 A JP2010001889 A JP 2010001889A JP 2009141810 A JP2009141810 A JP 2009141810A JP 2009141810 A JP2009141810 A JP 2009141810A JP 2010001889 A JP2010001889 A JP 2010001889A
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- Prior art keywords
- airfoil
- inflow
- refrigerant
- turbulator
- cross hole
- 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.)
- Granted
Links
- 238000005192 partition Methods 0.000 claims abstract description 36
- 238000001816 cooling Methods 0.000 claims description 66
- 239000003507 refrigerant Substances 0.000 claims description 49
- 238000000034 method Methods 0.000 abstract description 3
- 230000000875 corresponding effect Effects 0.000 description 42
- 239000010408 film Substances 0.000 description 14
- 238000005266 casting Methods 0.000 description 11
- 230000008901 benefit Effects 0.000 description 7
- 239000000567 combustion gas Substances 0.000 description 7
- 238000013461 design Methods 0.000 description 7
- 239000007789 gas Substances 0.000 description 7
- 230000006872 improvement Effects 0.000 description 4
- 238000012546 transfer Methods 0.000 description 4
- 230000001154 acute effect Effects 0.000 description 3
- 239000000919 ceramic Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000010409 thin film Substances 0.000 description 1
Images
Classifications
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- 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
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
-
- 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
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- 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
-
- 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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
【解決手段】タービンエアフォイル12は、対向する前縁及び後縁32、34間において軸線方向に翼弦に渡って延びる加圧側壁及び吸引側壁24、26を有する。側壁24、26は、横方向に間隔を空けており、側壁24、26を橋絡する仕切り36により翼弦方向に分割され縦方向に延びる流路を定める。有孔部36は、その内部を斜めに延びる交差孔40の列を含む。
【選択図】図1
Description
図1に、ガスタービンエンジン内において使用するタービンロータブレード10の実施形態例を示す。ブレード10は、内部プラットフォーム14から一体的に外側へ延びるエアフォイル12を含み、内部プラットフォーム14は、エンジン内の支持ロータディスク(図示無し)の周囲にブレードを取り付けるために構成された従来のダブテール16と一体式に形成される。
Claims (10)
- タービンエアフォイル(12)であって、
対向する前縁及び後縁(32、34)間において、縦方向に翼幅に渡って延び、軸線方向に翼弦に渡って延びる加圧及び吸引側壁(24、26)であり、前記側壁(24、26)を橋絡する仕切り(36)により翼弦方向に分割され縦方向に延びる複数の流路(1乃至6)を定めるように、間に横方向に間隔を空け、
前記仕切り(36)の一枚は有孔であり、その内部を傾斜して通過し且つ前記有孔仕切り(36)の一方の側にある流入路(2、5)と、その反対側にある流出路(1、6)との間に渡って延びる交差孔(40)の縦列を有し、
前記交差孔(40)は、前記有孔仕切り(36)を介して、前記縦流入路(2、5)とは反対に縦方向へ傾斜して、内部を通して送られる冷媒の方向を反転させる、加圧及び吸引側壁(24、26)と、
前記流入路(2、5)内部において、前記加圧及び吸引側壁(24、26)の内側に並び、前記冷媒の二次流動を導入すると共に、前記交差孔(40)に対して縦方向に傾斜して局所的に温度の低い冷媒を前記交差孔(40)へ送るタービュレータ群(44)と、を備えるエアフォイル。 - 前記流入路(2、5)は、横方向の高さに対する翼弦方向の幅のアスペクト比を有し、
前記タービュレータ(44)は、1未満のアスペクト比に対して、前記有孔仕切り(36)において終了する第一の傾斜方向を有し、
前記タービュレータ(44)は、1より大きな前記アスペクト比に対して、前記有孔仕切り(36)において開始される逆の第二の傾斜方向を有する、請求項1記載のエアフォイル。 - 前記タービュレータ(44)のそれぞれは、前記流入路(2、5)を通る前記冷媒(20)を最初に受領する第一の開始端部(46)と、前記流入路(2、5)を通る前記冷媒を最後に受領する、縦方向反対側の第二の終了端部(48)とを有し、
前記タービュレータは、前記流入路(2、5)内において縦方向に傾斜し、前記開始及び終了端部(46、48)は、翼幅において異なる高さに位置する、請求項2記載のエアフォイル。 - 前記加圧及び吸引側壁(24、26)は、半径方向内側の根元(28)から半径方向外側の先端(30)まで翼幅に渡って縦方向に延び、
前記交差孔(40)は、前記流入路(2、5)から前記流出路(1、6)へ縦方向内側に傾斜する、請求項3記載のエアフォイル。 - 前記流出路(1)は、前記前縁(32)の直後に配置され、前記交差孔(40)は、前記前縁に向かって傾斜し、その裏側をインピンジメント冷却する、請求項3記載のエアフォイル。
- 前記タービュレータ(44)は、前記流入路(2)において縦方向に傾斜し、前記終了端部(48)が前記有孔仕切り(36)に隣接する状態となる、請求項5記載のエアフォイル。
- 前記側壁(24、26)の一方を介して、前記交差孔(40)と反対の傾斜方向へ傾斜するフィルム冷却孔(50)の列を更に備える、請求項6記載のエアフォイル。
- 前記交差孔(40)は、前記流入路(2)から前記流出路(1)へ縦方向内側に傾斜し、前記フィルム冷却孔(50)は、前記流出路(1)から前記一方の側壁(24、26)を介して、縦方向外側に傾斜する、請求項7記載のエアフォイル。
- 前記流出路(6)は、前記後縁(34)の直前に配置され、前記交差孔(40)は、前記後縁に向かって傾斜し、その前側をインピンジメント冷却する、請求項3記載のエアフォイル。
- 前記タービュレータ(44)は、前記流入路(2)において縦方向に傾斜し、前記開始端部(46)が前記有孔仕切り(36)に隣接する状態となる、請求項9記載のエアフォイル。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/141,238 US8210814B2 (en) | 2008-06-18 | 2008-06-18 | Crossflow turbine airfoil |
US12/141,238 | 2008-06-18 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2010001889A true JP2010001889A (ja) | 2010-01-07 |
JP5325664B2 JP5325664B2 (ja) | 2013-10-23 |
Family
ID=40937241
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2009141810A Expired - Fee Related JP5325664B2 (ja) | 2008-06-18 | 2009-06-15 | クロスフロータービンエアフォイル |
Country Status (5)
Country | Link |
---|---|
US (1) | US8210814B2 (ja) |
JP (1) | JP5325664B2 (ja) |
CA (1) | CA2668605C (ja) |
DE (1) | DE102009025960A1 (ja) |
GB (1) | GB2460936B (ja) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2013015062A (ja) * | 2011-07-04 | 2013-01-24 | Hitachi Ltd | ガスタービン翼 |
KR101883564B1 (ko) * | 2016-11-02 | 2018-07-30 | 두산중공업 주식회사 | 가스터빈 블레이드 |
JP2020112146A (ja) * | 2019-01-17 | 2020-07-27 | 三菱日立パワーシステムズ株式会社 | タービン動翼及びガスタービン |
Families Citing this family (29)
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US8167558B2 (en) * | 2009-01-19 | 2012-05-01 | Siemens Energy, Inc. | Modular serpentine cooling systems for turbine engine components |
CH705185A1 (de) * | 2011-06-29 | 2012-12-31 | Alstom Technology Ltd | Schaufel für eine Gasturbine sowie Verfahren zum Herstellen einer solchen Schaufel. |
US20130156602A1 (en) | 2011-12-16 | 2013-06-20 | United Technologies Corporation | Film cooled turbine component |
US9138804B2 (en) | 2012-01-11 | 2015-09-22 | United Technologies Corporation | Core for a casting process |
US8920122B2 (en) | 2012-03-12 | 2014-12-30 | Siemens Energy, Inc. | Turbine airfoil with an internal cooling system having vortex forming turbulators |
US8936067B2 (en) * | 2012-10-23 | 2015-01-20 | Siemens Aktiengesellschaft | Casting core for a cooling arrangement for a gas turbine component |
US9995150B2 (en) * | 2012-10-23 | 2018-06-12 | Siemens Aktiengesellschaft | Cooling configuration for a gas turbine engine airfoil |
EP2948634B1 (en) * | 2013-01-24 | 2021-08-25 | Raytheon Technologies Corporation | Gas turbine engine component with angled aperture impingement |
US10316668B2 (en) | 2013-02-05 | 2019-06-11 | United Technologies Corporation | Gas turbine engine component having curved turbulator |
US9638057B2 (en) | 2013-03-14 | 2017-05-02 | Rolls-Royce North American Technologies, Inc. | Augmented cooling system |
US20150322797A1 (en) * | 2014-05-09 | 2015-11-12 | United Technologies Corporation | Blade element cross-ties |
US10119404B2 (en) * | 2014-10-15 | 2018-11-06 | Honeywell International Inc. | Gas turbine engines with improved leading edge airfoil cooling |
US10190420B2 (en) * | 2015-02-10 | 2019-01-29 | United Technologies Corporation | Flared crossovers for airfoils |
US10156157B2 (en) * | 2015-02-13 | 2018-12-18 | United Technologies Corporation | S-shaped trip strips in internally cooled components |
US10307816B2 (en) | 2015-10-26 | 2019-06-04 | United Technologies Corporation | Additively manufactured core for use in casting an internal cooling circuit of a gas turbine engine component |
US10226812B2 (en) | 2015-12-21 | 2019-03-12 | United Technologies Corporation | Additively manufactured core for use in casting an internal cooling circuit of a gas turbine engine component |
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US10697301B2 (en) | 2017-04-07 | 2020-06-30 | General Electric Company | Turbine engine airfoil having a cooling circuit |
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US10370976B2 (en) | 2017-08-17 | 2019-08-06 | United Technologies Corporation | Directional cooling arrangement for airfoils |
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JP6996947B2 (ja) * | 2017-11-09 | 2022-01-17 | 三菱パワー株式会社 | タービン翼及びガスタービン |
US10570748B2 (en) | 2018-01-10 | 2020-02-25 | United Technologies Corporation | Impingement cooling arrangement for airfoils |
US11209224B2 (en) | 2018-04-19 | 2021-12-28 | Raytheon Technologies Corporation | Mixing between flow channels of cast plate heat exchanger |
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US20200182068A1 (en) * | 2018-12-05 | 2020-06-11 | United Technologies Corporation | Axial flow cooling scheme with structural rib for a gas turbine engine |
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KR102161765B1 (ko) * | 2019-02-22 | 2020-10-05 | 두산중공업 주식회사 | 터빈용 에어포일, 이를 포함하는 터빈 |
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2009
- 2009-06-10 DE DE102009025960A patent/DE102009025960A1/de not_active Withdrawn
- 2009-06-11 GB GB0910051.2A patent/GB2460936B/en not_active Expired - Fee Related
- 2009-06-11 CA CA2668605A patent/CA2668605C/en not_active Expired - Fee Related
- 2009-06-15 JP JP2009141810A patent/JP5325664B2/ja not_active Expired - Fee Related
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JP2008128234A (ja) * | 2006-11-20 | 2008-06-05 | General Electric Co <Ge> | 二重送り蛇行冷却ブレード |
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JP2013015062A (ja) * | 2011-07-04 | 2013-01-24 | Hitachi Ltd | ガスタービン翼 |
KR101883564B1 (ko) * | 2016-11-02 | 2018-07-30 | 두산중공업 주식회사 | 가스터빈 블레이드 |
JP2020112146A (ja) * | 2019-01-17 | 2020-07-27 | 三菱日立パワーシステムズ株式会社 | タービン動翼及びガスタービン |
JP7224928B2 (ja) | 2019-01-17 | 2023-02-20 | 三菱重工業株式会社 | タービン動翼及びガスタービン |
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GB2460936A (en) | 2009-12-23 |
CA2668605C (en) | 2016-10-04 |
JP5325664B2 (ja) | 2013-10-23 |
GB2460936B (en) | 2012-11-28 |
US20090317234A1 (en) | 2009-12-24 |
GB0910051D0 (en) | 2009-07-22 |
CA2668605A1 (en) | 2009-12-18 |
US8210814B2 (en) | 2012-07-03 |
DE102009025960A1 (de) | 2009-12-24 |
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