JP5264058B2 - 固定タービン翼形部 - Google Patents
固定タービン翼形部 Download PDFInfo
- Publication number
- JP5264058B2 JP5264058B2 JP2006020107A JP2006020107A JP5264058B2 JP 5264058 B2 JP5264058 B2 JP 5264058B2 JP 2006020107 A JP2006020107 A JP 2006020107A JP 2006020107 A JP2006020107 A JP 2006020107A JP 5264058 B2 JP5264058 B2 JP 5264058B2
- Authority
- JP
- Japan
- Prior art keywords
- turbine
- vane
- turbine assembly
- nozzle
- blade
- 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.)
- Expired - Fee Related
Links
- 238000010926 purge Methods 0.000 claims description 16
- 239000007789 gas Substances 0.000 description 16
- 239000000567 combustion gas Substances 0.000 description 4
- 230000007704 transition Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000013508 migration Methods 0.000 description 1
- 230000005012 migration Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000001960 triggered effect 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- 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
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
-
- 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
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
122 ノズルベーン
126 タービンブレード
128 パージキャビティ
130 ノズルセグメント
132 前縁
134 後縁
136 根元
138 先端
140 正圧側面
142 負圧側面
144 外側バンド
146 内側バンド
148 内側流路面
150 前面
152 後面
154 ブレンデッドコーナ部
Claims (5)
- ガスタービンエンジン(10)用のタービン組立体であって、
ベーン(122)、このベーンの根元(136)、先端(138)、前縁(132)、後縁(134)並びに対向する正圧(140)及び負圧(142)側面を有する翼形形状のベーン(122)と;
前記ベーン(122)の根元(136)に取付けられ、それぞれその前端部及び後端部において前面(150)及び後面(152)によって境界付けられた内側流路面(148)を含む弓形の内側バンド(146)と;
を含むノズルセグメント(130)と、
前記ノズルセグメント(130)の後方にかつ該ノズルセグメント(130)と流れ連通した状態で配置され、第2の内側流路面(148)を形成した弓形のブレードプラットフォームを含む回転可能に支持されたタービンブレードと、
前記ノズルセグメント(130)と前記タービンブレードとの間に形成され、エンジンの二次流路と流れ連通した状態になっているパージキャビティ(128)とを備え、
前記内側バンド(146)の内側流路面(148)と前記後面(152)との接合部が、凸状湾曲ブレンデッドコーナ部(154)を形成し、前記パージキャビティ(128)内に旋回ベーン(122)流を誘発するよう該ブレンデッドコーナ部(154)の断面輪郭が所定の円弧半径によって形成されている
ことを特徴とするタービン組立体。 - 該タービン組立体が、前記ベーンの先端(138)に取付けられた弓形の外側バンドセグメント(144)をさらに含み、前記外側バンドセグメント(144)が、外側流路面(148)を有することを特徴とする請求項1記載のタービン組立体。
- 複数の前記外側バンドセグメント(144)が、並んで配置されて円形ノズルリングを形成していることを特徴とする請求項2記載のタービン組立体。
- 前記半径が、0.381mm(0.015インチ)よりも大きいことを特徴とする請求項1記載のタービン組立体。
- 前記ブレンデッドコーナ部(154)が、前記内側流路面(148)の接線であり、軸対称に形成されていることを特徴とする請求項1記載のタービン組立体。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/907,476 US7249928B2 (en) | 2005-04-01 | 2005-04-01 | Turbine nozzle with purge cavity blend |
US10/907,476 | 2005-04-01 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2006283755A JP2006283755A (ja) | 2006-10-19 |
JP5264058B2 true JP5264058B2 (ja) | 2013-08-14 |
Family
ID=36061083
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2006020107A Expired - Fee Related JP5264058B2 (ja) | 2005-04-01 | 2006-01-30 | 固定タービン翼形部 |
Country Status (4)
Country | Link |
---|---|
US (1) | US7249928B2 (ja) |
JP (1) | JP5264058B2 (ja) |
FR (1) | FR2883920B1 (ja) |
GB (1) | GB2427004B (ja) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7578653B2 (en) * | 2006-12-19 | 2009-08-25 | General Electric Company | Ovate band turbine stage |
US20080145208A1 (en) * | 2006-12-19 | 2008-06-19 | General Electric Company | Bullnose seal turbine stage |
EP2055902A1 (en) * | 2007-10-31 | 2009-05-06 | Siemens Aktiengesellschaft | Turbine for a thermal power plant comprising a rotor bucket and a guide bucket |
EP2055896A1 (en) * | 2007-10-31 | 2009-05-06 | Siemens Aktiengesellschaft | Bucket for a turbine of a thermal power plant having a foot section |
US8657579B2 (en) * | 2010-08-27 | 2014-02-25 | General Electric Company | Blade for use with a rotary machine and method of assembling same rotary machine |
US9216428B2 (en) * | 2011-11-04 | 2015-12-22 | Nsk Ltd. | Spindle system and electrostatic painting system |
EP2607625B1 (de) * | 2011-12-20 | 2021-09-08 | MTU Aero Engines AG | Turbomaschine und turbomaschinenstufe |
US8769816B2 (en) | 2012-02-07 | 2014-07-08 | Siemens Aktiengesellschaft | Method of assembling a gas turbine engine |
US9175567B2 (en) | 2012-02-29 | 2015-11-03 | United Technologies Corporation | Low loss airfoil platform trailing edge |
US9181816B2 (en) | 2013-01-23 | 2015-11-10 | Siemens Aktiengesellschaft | Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine |
US10132182B2 (en) * | 2014-11-12 | 2018-11-20 | United Technologies Corporation | Platforms with leading edge features |
EP3020929A1 (en) * | 2014-11-17 | 2016-05-18 | United Technologies Corporation | Airfoil platform rim seal assembly |
US10030538B2 (en) | 2015-11-05 | 2018-07-24 | General Electric Company | Gas turbine engine with a vane having a cooling air turning nozzle |
US11156116B2 (en) * | 2019-04-08 | 2021-10-26 | Honeywell International Inc. | Turbine nozzle with reduced leakage feather seals |
US11415016B2 (en) * | 2019-11-11 | 2022-08-16 | Rolls-Royce Plc | Turbine section assembly with ceramic matrix composite components and interstage sealing features |
CN112096653B (zh) * | 2020-11-18 | 2021-01-19 | 中国航发上海商用航空发动机制造有限责任公司 | 叶片缘板、叶片环、叶轮盘以及燃气涡轮发动机 |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3854842A (en) * | 1973-04-30 | 1974-12-17 | Gen Electric | Rotor blade having improved tip cap |
GB2032531B (en) | 1978-10-26 | 1982-09-22 | Rolls Royce | Air cooled gas turbine rotor |
US4348157A (en) * | 1978-10-26 | 1982-09-07 | Rolls-Royce Limited | Air cooled turbine for a gas turbine engine |
JPS5951104A (ja) * | 1982-09-17 | 1984-03-24 | Hitachi Ltd | タ−ビン段落の内部構造 |
GB2233401A (en) | 1989-06-21 | 1991-01-09 | Rolls Royce Plc | Improvements in or relating to gas turbine engines |
US5181728A (en) * | 1991-09-23 | 1993-01-26 | General Electric Company | Trenched brush seal |
US5252026A (en) * | 1993-01-12 | 1993-10-12 | General Electric Company | Gas turbine engine nozzle |
JPH0680801U (ja) * | 1993-04-28 | 1994-11-15 | 石川島播磨重工業株式会社 | 静翼セグメントの取付構造 |
GB2281356B (en) | 1993-08-20 | 1997-01-29 | Rolls Royce Plc | Gas turbine engine turbine |
US6375419B1 (en) * | 1995-06-02 | 2002-04-23 | United Technologies Corporation | Flow directing element for a turbine engine |
US6183192B1 (en) * | 1999-03-22 | 2001-02-06 | General Electric Company | Durable turbine nozzle |
US6142734A (en) * | 1999-04-06 | 2000-11-07 | General Electric Company | Internally grooved turbine wall |
US6375415B1 (en) | 2000-04-25 | 2002-04-23 | General Electric Company | Hook support for a closed circuit fluid cooled gas turbine nozzle stage segment |
US6425738B1 (en) * | 2000-05-11 | 2002-07-30 | General Electric Company | Accordion nozzle |
US6354797B1 (en) * | 2000-07-27 | 2002-03-12 | General Electric Company | Brazeless fillet turbine nozzle |
US6524070B1 (en) * | 2000-08-21 | 2003-02-25 | General Electric Company | Method and apparatus for reducing rotor assembly circumferential rim stress |
US6579061B1 (en) * | 2001-07-27 | 2003-06-17 | General Electric Company | Selective step turbine nozzle |
US6830432B1 (en) * | 2003-06-24 | 2004-12-14 | Siemens Westinghouse Power Corporation | Cooling of combustion turbine airfoil fillets |
-
2005
- 2005-04-01 US US10/907,476 patent/US7249928B2/en not_active Expired - Fee Related
-
2006
- 2006-01-30 GB GB0601788A patent/GB2427004B/en not_active Expired - Fee Related
- 2006-01-30 JP JP2006020107A patent/JP5264058B2/ja not_active Expired - Fee Related
- 2006-02-01 FR FR0600930A patent/FR2883920B1/fr not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
GB2427004A (en) | 2006-12-13 |
US7249928B2 (en) | 2007-07-31 |
US20070128021A1 (en) | 2007-06-07 |
GB0601788D0 (en) | 2006-03-08 |
FR2883920B1 (fr) | 2013-11-01 |
JP2006283755A (ja) | 2006-10-19 |
FR2883920A1 (fr) | 2006-10-06 |
GB2427004B (en) | 2011-05-04 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP5264058B2 (ja) | 固定タービン翼形部 | |
US7371046B2 (en) | Turbine airfoil with variable and compound fillet | |
CA2528049C (en) | Airfoil platform impingement cooling | |
EP2199543B1 (en) | Rotor blade for a gas turbine engine and method of designing an airfoil | |
CA2565867C (en) | Shockwave-induced boundary layer bleed for transonic gas turbine | |
JP5156362B2 (ja) | 弓形要素を支持するための冠状レール | |
EP1693552A2 (en) | A turbine blade | |
EP2666964A2 (en) | Gas turbine engine blades with cooling hole trenches | |
CA2909468A1 (en) | Engine component for a gas turbine engine | |
JP2017106452A (ja) | フィレットフィルム孔を有するガスタービンエンジン | |
US20170211393A1 (en) | Gas turbine aerofoil trailing edge | |
CA2956979A1 (en) | Impingement holes for a turbine engine component | |
JP2010156338A (ja) | タービン翼付け根構成 | |
JP2017141825A (ja) | ガスタービンエンジン用の翼形部 | |
CN106988889B (zh) | 用于涡轮发动机的涡轮后框架 | |
JP2019007478A (ja) | ロータブレード先端部 | |
US20210372288A1 (en) | Compressor stator with leading edge fillet | |
JP2019056366A (ja) | タービンエンジン翼形部用のシールド | |
JP2009209745A (ja) | 軸流式ターボ機械のタービン段、及びガスタービン | |
CN114753889A (zh) | 具有一组凹痕的翼型件的涡轮发动机 | |
EP3299587B1 (en) | Gas turbine engine airfoil | |
CN110872952A (zh) | 具有中空销的涡轮发动机的部件 | |
US11939880B1 (en) | Airfoil assembly with flow surface | |
JP2015514920A (ja) | 耐久性があるタービンベーン |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20090127 |
|
A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20100929 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20101005 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20101224 |
|
RD02 | Notification of acceptance of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7422 Effective date: 20101224 |
|
RD04 | Notification of resignation of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7424 Effective date: 20101224 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20110104 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20110330 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20110719 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20111013 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20111018 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20120118 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20120724 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20121019 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20121024 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20130123 |
|
TRDD | Decision of grant or rejection written | ||
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20130402 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20130430 |
|
R150 | Certificate of patent or registration of utility model |
Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
LAPS | Cancellation because of no payment of annual fees |