JP2007077986A - 翼端棚を有するタービンエーロフォイル湾曲スクイーラ翼端 - Google Patents
翼端棚を有するタービンエーロフォイル湾曲スクイーラ翼端 Download PDFInfo
- Publication number
- JP2007077986A JP2007077986A JP2006245244A JP2006245244A JP2007077986A JP 2007077986 A JP2007077986 A JP 2007077986A JP 2006245244 A JP2006245244 A JP 2006245244A JP 2006245244 A JP2006245244 A JP 2006245244A JP 2007077986 A JP2007077986 A JP 2007077986A
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- Prior art keywords
- airfoil
- tip
- pressure side
- wing tip
- wall
- 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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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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/712—Shape curved concave
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
【解決手段】エーロフォイル(18)は、圧力側壁(20)および吸込側壁(22)の間に延びる翼端キャップ(32)、および翼端キャップ(32)から外へ放射状に延びて、間に翼端空洞(38)を定める相隔てた吸込側壁(34)および圧力側翼端(36)を含む。圧力側翼端壁(34)は、連続凹状湾曲弓形部分(52)を含み、少なくともその一セクションは、エーロフォイル(18)の放射軸から外に向かって周囲に延びる。圧力側翼端壁(34)の少なくとも一部は、圧力側壁(20)から凹まされ、外に面する翼端棚(56)を定め、それにより、圧力側翼端壁(34)および翼端棚(56)は、それらの間にトラフ(58)を定める。
【選択図】図3
Description
12 ダブテール
14 ブレードシャンク
16 翼台
18 エーロフォイル
20 凹状圧力側壁
22 凸状圧力側壁
24 前縁
26 後縁
28 翼根部
30 翼端
32 翼端キャップ
34 圧力側翼端壁
36 吸込側翼端壁
38 翼端空洞
40 内面
42 外面
44 翼端表面
46 内面
48 外面
50 翼端表面
52 弓形部分
54 翼端コーナー
56 翼端棚
58 トラフ
60 第1の冷却孔
62 入口
64 内側空洞
66 出口
68 第2の冷却孔
Claims (10)
- 翼根部(28)、翼端(30)、前縁(24)、後縁(26)、ならびに概ね放射軸にそって延びる対向する圧力側壁(20)および吸込側壁(22)を備えるガスタービンエンジン用のエーロフォイル(18)であって、
前記圧力側壁(20)と吸込側壁(22)との間に延びる翼端キャップ(32)と、
前記翼端キャップ(32)から放射状に外へ延び、間に翼端空洞(38)を定める相隔てた吸込側(36)および圧力側翼端壁(34)とを備え、
前記圧力側翼端壁(34)は連続凹状湾曲弓形部分(52)を備え、少なくともそのひとつのセクションは前記エーロフォイル(18)の放射軸から外に向かって周囲に延び、且つ前記圧力側翼端壁(34)は前記圧力側壁(20)から凹まされて外に面する翼端棚(56)を定め、前記圧力側翼端壁(34)および前記翼端棚(56)がその間にトラフを形成するエーロフォイル(18)。 - 前記翼端棚(56)を通って延びる複数の第1の冷却孔(60)をさらに備え、
前記第1の冷却孔(60)はそれぞれ、冷却用空気源と流れ連通するように配置されている入口(62)と前記トラフ(58)と流れ連通するように配置されている出口(66)とを備える、請求項1記載のエーロフォイル(18)。 - 前記翼端棚(56)は、前記前縁(24)から前記後縁(26)までの前記エーロフォイル(18)の軸方向長さの実質的全体にわたって延びる請求項1記載のエーロフォイル(18)。
- 前記エーロフォイル(18)は、連続して並ぶ、前縁領域、中間翼弦領域、および後縁領域を備え、前記翼端棚(56)は、前記中間翼弦領域内に実質的に含まれる請求項1記載のエーロフォイル(18)。
- 前記弓形部分(52)は、前記前縁(24)から前記後縁(26)までの前記エーロフォイル(18)の軸方向長さの実質的全体にわたって延びる請求項4記載のエーロフォイル(18)。
- 前記弓形部分(52)は、前記前縁(24)から前記後縁(26)までの前記エーロフォイル(18)の全長よりも実質的に短い長さにわたって延びる請求項4記載のエーロフォイル(18)。
- 前記圧力側翼端壁(34)は、半径方向に面する翼端表面(44)により連結されている相隔てた内面(40)および外面(42)を備え、
翼端コーナー(54)は、前記外面(42)と前記翼端面(44)との接合点で定められる請求項1記載のエーロフォイル(18)。 - 前記翼端コーナー(54)は、周方向で測ったとき前記圧力側壁(20)の外面(42)を越えて延びる請求項7記載のエーロフォイル(18)。
- 前記翼端コーナー(54)は、周方向で測ったとき前記圧力側壁(20)の外面(42)を越えて延びない請求項7記載のエーロフォイル(18)。
- さらに、前記圧力側壁(20)内に配置され、冷却用空気源から冷却用空気を受け取り、前記圧力側翼端壁(34)の前記弓形部分(52)を乗り越えて冷却膜内に放出するように適合されている複数の第2の冷却孔(68)を備える請求項1記載のエーロフォイル(18)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/162,434 US7281894B2 (en) | 2005-09-09 | 2005-09-09 | Turbine airfoil curved squealer tip with tip shelf |
US11/162,434 | 2005-09-09 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2007077986A true JP2007077986A (ja) | 2007-03-29 |
JP5289694B2 JP5289694B2 (ja) | 2013-09-11 |
Family
ID=37216110
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2006245244A Expired - Fee Related JP5289694B2 (ja) | 2005-09-09 | 2006-09-11 | 翼端棚を有するタービンエーロフォイル湾曲スクイーラ翼端 |
Country Status (5)
Country | Link |
---|---|
US (1) | US7281894B2 (ja) |
EP (1) | EP1762702B1 (ja) |
JP (1) | JP5289694B2 (ja) |
CN (1) | CN1928325B (ja) |
CA (1) | CA2558276C (ja) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
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JP2011089517A (ja) * | 2009-10-21 | 2011-05-06 | General Electric Co <Ge> | タービン及びタービンブレードウィングレット |
JP2014533794A (ja) * | 2011-11-17 | 2014-12-15 | スネクマ | 正圧側に向かってオフセットされた先端部および冷却チャネルを備えるガスタービンブレード |
JP2016211547A (ja) * | 2015-04-29 | 2016-12-15 | ゼネラル・エレクトリック・カンパニイ | フレア状先端を有するロータブレード |
US11371361B2 (en) | 2017-08-16 | 2022-06-28 | Siemens Energy Global GmbH & Co. KG | Turbine blade and corresponding servicing method |
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US7473073B1 (en) * | 2006-06-14 | 2009-01-06 | Florida Turbine Technologies, Inc. | Turbine blade with cooled tip rail |
US7597539B1 (en) * | 2006-09-27 | 2009-10-06 | Florida Turbine Technologies, Inc. | Turbine blade with vortex cooled end tip rail |
US8167572B2 (en) * | 2008-07-14 | 2012-05-01 | Pratt & Whitney Canada Corp. | Dynamically tuned turbine blade growth pocket |
US8092178B2 (en) * | 2008-11-28 | 2012-01-10 | Pratt & Whitney Canada Corp. | Turbine blade for a gas turbine engine |
US8186965B2 (en) * | 2009-05-27 | 2012-05-29 | General Electric Company | Recovery tip turbine blade |
US9181814B2 (en) | 2010-11-24 | 2015-11-10 | United Technology Corporation | Turbine engine compressor stator |
GB201100957D0 (en) * | 2011-01-20 | 2011-03-02 | Rolls Royce Plc | Rotor blade |
US8858167B2 (en) | 2011-08-18 | 2014-10-14 | United Technologies Corporation | Airfoil seal |
US10087764B2 (en) | 2012-03-08 | 2018-10-02 | Pratt & Whitney Canada Corp. | Airfoil for gas turbine engine |
US9091177B2 (en) | 2012-03-14 | 2015-07-28 | United Technologies Corporation | Shark-bite tip shelf cooling configuration |
US9228442B2 (en) | 2012-04-05 | 2016-01-05 | United Technologies Corporation | Turbine airfoil tip shelf and squealer pocket cooling |
US9284845B2 (en) | 2012-04-05 | 2016-03-15 | United Technologies Corporation | Turbine airfoil tip shelf and squealer pocket cooling |
US9470096B2 (en) | 2012-07-26 | 2016-10-18 | General Electric Company | Turbine bucket with notched squealer tip |
US9045988B2 (en) | 2012-07-26 | 2015-06-02 | General Electric Company | Turbine bucket with squealer tip |
FR2997442B1 (fr) * | 2012-10-31 | 2018-05-18 | Safran Aircraft Engines | Aube pourvue d'une ailerette pouvant etre fabriquee par fonderie a la cire perdue |
US10655473B2 (en) | 2012-12-13 | 2020-05-19 | United Technologies Corporation | Gas turbine engine turbine blade leading edge tip trench cooling |
US8920124B2 (en) | 2013-02-14 | 2014-12-30 | Siemens Energy, Inc. | Turbine blade with contoured chamfered squealer tip |
US10760499B2 (en) | 2013-03-14 | 2020-09-01 | Pratt & Whitney Canada Corp. | Turbo-machinery rotors with rounded tip edge |
US9810070B2 (en) | 2013-05-15 | 2017-11-07 | General Electric Company | Turbine rotor blade for a turbine section of a gas turbine |
US9638041B2 (en) | 2013-10-23 | 2017-05-02 | General Electric Company | Turbine bucket having non-axisymmetric base contour |
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US9551226B2 (en) | 2013-10-23 | 2017-01-24 | General Electric Company | Turbine bucket with endwall contour and airfoil profile |
US9347320B2 (en) | 2013-10-23 | 2016-05-24 | General Electric Company | Turbine bucket profile yielding improved throat |
US9670784B2 (en) | 2013-10-23 | 2017-06-06 | General Electric Company | Turbine bucket base having serpentine cooling passage with leading edge cooling |
US9376927B2 (en) | 2013-10-23 | 2016-06-28 | General Electric Company | Turbine nozzle having non-axisymmetric endwall contour (EWC) |
US9528379B2 (en) | 2013-10-23 | 2016-12-27 | General Electric Company | Turbine bucket having serpentine core |
EP3068975B1 (en) * | 2013-11-11 | 2020-11-25 | United Technologies Corporation | Gas turbine engine component and corresponding methods of manufacturing |
US10053992B2 (en) * | 2015-07-02 | 2018-08-21 | United Technologies Corporation | Gas turbine engine airfoil squealer pocket cooling hole configuration |
FR3043715B1 (fr) * | 2015-11-16 | 2020-11-06 | Snecma | Aube de turbine comprenant une pale avec baignoire comportant un intrados incurve dans la region du sommet de pale |
US10436038B2 (en) * | 2015-12-07 | 2019-10-08 | General Electric Company | Turbine engine with an airfoil having a tip shelf outlet |
US10253637B2 (en) * | 2015-12-11 | 2019-04-09 | General Electric Company | Method and system for improving turbine blade performance |
WO2018004766A1 (en) * | 2016-05-24 | 2018-01-04 | General Electric Company | Airfoil and blade for a turbine engine, and corresponding method of flowing a cooling fluid |
WO2018063353A1 (en) * | 2016-09-30 | 2018-04-05 | Siemens Aktiengesellschaft | Turbine blade and squealer tip |
US10533429B2 (en) | 2017-02-27 | 2020-01-14 | Rolls-Royce Corporation | Tip structure for a turbine blade with pressure side and suction side rails |
FR3065483B1 (fr) * | 2017-04-24 | 2020-08-07 | Safran Aircraft Engines | Dispositif d'etancheite entre rotor et stator de turbomachine |
CN111448367A (zh) * | 2017-12-19 | 2020-07-24 | 赛峰直升机发动机 | 涡轮发动机叶轮 |
KR20190127024A (ko) * | 2018-05-03 | 2019-11-13 | 두산중공업 주식회사 | 터빈 블레이드 및 상기 터빈 블레이드를 포함하는 가스 터빈 |
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-
2005
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-
2006
- 2006-08-31 CA CA2558276A patent/CA2558276C/en not_active Expired - Fee Related
- 2006-09-04 EP EP06254602A patent/EP1762702B1/en not_active Expired - Fee Related
- 2006-09-08 CN CN2006101513842A patent/CN1928325B/zh active Active
- 2006-09-11 JP JP2006245244A patent/JP5289694B2/ja not_active Expired - Fee Related
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US5282721A (en) * | 1991-09-30 | 1994-02-01 | United Technologies Corporation | Passive clearance system for turbine blades |
WO2005014978A1 (en) * | 2002-07-16 | 2005-02-17 | General Electric Company | Turbine blade having angled squealer tip |
JP2004124813A (ja) * | 2002-10-02 | 2004-04-22 | Ishikawajima Harima Heavy Ind Co Ltd | 回転機械の動翼 |
US20040179940A1 (en) * | 2003-03-12 | 2004-09-16 | Florida Turbine Technologies, Inc. | Multi-metered film cooled blade tip |
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2011089517A (ja) * | 2009-10-21 | 2011-05-06 | General Electric Co <Ge> | タービン及びタービンブレードウィングレット |
JP2014533794A (ja) * | 2011-11-17 | 2014-12-15 | スネクマ | 正圧側に向かってオフセットされた先端部および冷却チャネルを備えるガスタービンブレード |
JP2016211547A (ja) * | 2015-04-29 | 2016-12-15 | ゼネラル・エレクトリック・カンパニイ | フレア状先端を有するロータブレード |
US11371361B2 (en) | 2017-08-16 | 2022-06-28 | Siemens Energy Global GmbH & Co. KG | Turbine blade and corresponding servicing method |
Also Published As
Publication number | Publication date |
---|---|
EP1762702B1 (en) | 2011-11-09 |
US20070059173A1 (en) | 2007-03-15 |
EP1762702A3 (en) | 2008-10-29 |
CA2558276C (en) | 2014-10-07 |
US7281894B2 (en) | 2007-10-16 |
CN1928325A (zh) | 2007-03-14 |
CN1928325B (zh) | 2011-11-16 |
JP5289694B2 (ja) | 2013-09-11 |
EP1762702A2 (en) | 2007-03-14 |
CA2558276A1 (en) | 2007-03-09 |
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