JP5410014B2 - 最新式ブースタステータベーン - Google Patents
最新式ブースタステータベーン Download PDFInfo
- Publication number
- JP5410014B2 JP5410014B2 JP2007307216A JP2007307216A JP5410014B2 JP 5410014 B2 JP5410014 B2 JP 5410014B2 JP 2007307216 A JP2007307216 A JP 2007307216A JP 2007307216 A JP2007307216 A JP 2007307216A JP 5410014 B2 JP5410014 B2 JP 5410014B2
- Authority
- JP
- Japan
- Prior art keywords
- booster
- root
- angle
- stator vane
- 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
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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
-
- 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
-
- 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)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Geometry (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
8 圧縮段
11 入口案内ベーン段
14 複数のロータブレード
15 縦方向中心軸線
17 ステータ段
18 ロータ段
18 複数のロータ段
19 ロータハブ
40 ステータベーン
42 ベーン前縁
43 ベーン後縁
44 ベーン正圧側面
45 ベーン負圧側面
46 根元
48 先端
50 ロータブレード翼形部
52 ブレード前縁
53 ブレード後縁
54 ブレード根元
55 ブレード先端
56 ブレード正圧側面
57 ブレード負圧側面
144 出口スワール分布プロファイル
146 第1の半径位置
147 第1のスパン位置
148 中間半径位置
151 ブレード第1の高さ位置
155 ブレード内側スパン領域
156 ブレード外側スパン領域
252 上反角分布
300 横方向ブレード翼形部セクション
302 最大ブレード翼形部断面厚さ
303 相対距離
Claims (6)
- ガスタービンエンジン(5)用のステータベーン(40)であって、
前縁及び後縁(42、43)間でかつ長手方向に根元(46)及び先端(48)間で延びる正圧及び負圧側面(44、45)を含み、
前記後縁(43)が、
出口スワール角が、
第1の半径位置(146)と、該第1の半径位置(146)及び前記先端(48)の間の中間半径位置(148)との間で増加し、
前記中間半径位置(148)において最大値を有し、
前記中間半径位置(148)と前記先端(48)との間で実質的に一定のままである
ような前記根元(46)から前記先端(48)までの出口スワール角分布プロファイル(144)を有する、
ステータベーン(40)。 - 前記中間半径位置(148)が、前記根元(46)から50%よりも大きいスパン高さの位置にある、請求項1記載のステータベーン(40)。
- 前記中間半径位置(148)が、前記根元(46)から60%から80%のスパン高さの位置にある、請求項1記載のステータベーン(40)。
- ガスタービンエンジン用のステータベーン(40)であって、
前縁及び後縁(42、43)間でかつ長手方向に根元(46)及び先端(48)間で延びる正圧及び負圧側面(44、45)を含み、
前記後縁(43)が、
出口スワール角が、
第1の半径位置(146)と、該第1の半径位置(146)及び前記先端(48)の間の中間半径位置(148)との間で増加し、
前記中間半径位置(148)において最大値を有し、
前記中間半径位置(148)と前記先端(48)との間で実質的に一定のままである
ような前記根元(46)から前記先端(48)までの出口スワール角分布プロファイルを有し、
前記前縁(42)が、前記根元(46)から該根元(46)及び前記先端(48)間の第1のスパン位置(147)までの前方スイープ角と前記第1のスパン位置(147)及び前記先端(48)間の後方スイープ角とを有する、
ステータベーン(40)。 - 前記中間半径位置(148)が、前記根元(46)から50%より大きいスパン高さの位置にある、請求項4記載のステータベーン(40)。
- 前記中間半径位置(148)が、前記根元(46)から60%〜80%のスパン高さの位置にある、請求項4記載のステータベーン(40)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/606,728 | 2006-11-30 | ||
US11/606,728 US8087884B2 (en) | 2006-11-30 | 2006-11-30 | Advanced booster stator vane |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2008138677A JP2008138677A (ja) | 2008-06-19 |
JP5410014B2 true JP5410014B2 (ja) | 2014-02-05 |
Family
ID=39125207
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2007307216A Expired - Fee Related JP5410014B2 (ja) | 2006-11-30 | 2007-11-28 | 最新式ブースタステータベーン |
Country Status (4)
Country | Link |
---|---|
US (1) | US8087884B2 (ja) |
EP (1) | EP1930600B1 (ja) |
JP (1) | JP5410014B2 (ja) |
CA (1) | CA2610541C (ja) |
Families Citing this family (45)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7967571B2 (en) | 2006-11-30 | 2011-06-28 | General Electric Company | Advanced booster rotor blade |
US8292574B2 (en) | 2006-11-30 | 2012-10-23 | General Electric Company | Advanced booster system |
US7758306B2 (en) * | 2006-12-22 | 2010-07-20 | General Electric Company | Turbine assembly for a gas turbine engine and method of manufacturing the same |
EP2369136B1 (fr) * | 2010-03-12 | 2012-12-19 | Techspace Aero S.A. | Tambour multi-étage monobloc allégé de compresseur axial |
US9074483B2 (en) | 2011-03-25 | 2015-07-07 | General Electric Company | High camber stator vane |
US8702398B2 (en) | 2011-03-25 | 2014-04-22 | General Electric Company | High camber compressor rotor blade |
US8684698B2 (en) | 2011-03-25 | 2014-04-01 | General Electric Company | Compressor airfoil with tip dihedral |
US20130022473A1 (en) * | 2011-07-22 | 2013-01-24 | Ken Tran | Blades with decreasing exit flow angle |
ITTO20111009A1 (it) * | 2011-11-03 | 2013-05-04 | Avio Spa | Profilo aerodinamico di una turbina |
US8438832B1 (en) * | 2012-01-31 | 2013-05-14 | United Technologies Corporation | High turning fan exit stator |
WO2014149354A1 (en) | 2013-03-15 | 2014-09-25 | United Technologies Corporation | Geared turbofan engine having a reduced number of fan blades and improved acoustics |
FR3003598B1 (fr) * | 2013-03-20 | 2018-04-06 | Safran Aircraft Engines | Aube et angle de diedre d'aube |
EP2818635B1 (fr) * | 2013-06-25 | 2019-04-10 | Safran Aero Boosters SA | Tambour de compresseur de turbomachine axiale avec fixation mixte d'aubes |
FR3009589B1 (fr) * | 2013-08-12 | 2015-09-04 | Snecma | Aube de redresseur de turbomachine |
WO2015175044A2 (en) * | 2014-02-19 | 2015-11-19 | United Technologies Corporation | Gas turbine engine airfoil |
EP3108114B1 (en) | 2014-02-19 | 2021-12-08 | Raytheon Technologies Corporation | Gas turbine engine airfoil |
US10495106B2 (en) | 2014-02-19 | 2019-12-03 | United Technologies Corporation | Gas turbine engine airfoil |
WO2015126454A1 (en) | 2014-02-19 | 2015-08-27 | United Technologies Corporation | Gas turbine engine airfoil |
EP3108105B1 (en) | 2014-02-19 | 2021-05-12 | Raytheon Technologies Corporation | Gas turbine engine airfoil |
WO2015175045A2 (en) | 2014-02-19 | 2015-11-19 | United Technologies Corporation | Gas turbine engine airfoil |
EP3108109B1 (en) | 2014-02-19 | 2023-09-13 | Raytheon Technologies Corporation | Gas turbine engine fan blade |
US10465702B2 (en) | 2014-02-19 | 2019-11-05 | United Technologies Corporation | Gas turbine engine airfoil |
US20170175759A1 (en) * | 2014-02-19 | 2017-06-22 | United Technologies Corporation | Gas turbine engine airfoil |
EP3108103B1 (en) | 2014-02-19 | 2023-09-27 | Raytheon Technologies Corporation | Fan blade for a gas turbine engine |
US10584715B2 (en) | 2014-02-19 | 2020-03-10 | United Technologies Corporation | Gas turbine engine airfoil |
WO2015126453A1 (en) | 2014-02-19 | 2015-08-27 | United Technologies Corporation | Gas turbine engine airfoil |
WO2015126774A1 (en) | 2014-02-19 | 2015-08-27 | United Technologies Corporation | Gas turbine engine airfoil |
US10385866B2 (en) | 2014-02-19 | 2019-08-20 | United Technologies Corporation | Gas turbine engine airfoil |
EP3575551B1 (en) | 2014-02-19 | 2021-10-27 | Raytheon Technologies Corporation | Gas turbine engine airfoil |
WO2015178974A2 (en) | 2014-02-19 | 2015-11-26 | United Technologies Corporation | Gas turbine engine airfoil |
US10557477B2 (en) | 2014-02-19 | 2020-02-11 | United Technologies Corporation | Gas turbine engine airfoil |
EP4279747A3 (en) | 2014-02-19 | 2024-03-13 | RTX Corporation | Turbofan engine with geared architecture and lpc blades |
EP4279706A3 (en) | 2014-02-19 | 2024-02-28 | RTX Corporation | Turbofan engine with geared architecture and lpc blade airfoils |
US9599064B2 (en) | 2014-02-19 | 2017-03-21 | United Technologies Corporation | Gas turbine engine airfoil |
JP6468414B2 (ja) * | 2014-08-12 | 2019-02-13 | 株式会社Ihi | 圧縮機静翼、軸流圧縮機、及びガスタービン |
US10060263B2 (en) * | 2014-09-15 | 2018-08-28 | United Technologies Corporation | Incidence-tolerant, high-turning fan exit stator |
FR3040071B1 (fr) * | 2015-08-11 | 2020-03-27 | Safran Aircraft Engines | Aube de rotor de turbomachine |
US11428241B2 (en) * | 2016-04-22 | 2022-08-30 | Raytheon Technologies Corporation | System for an improved stator assembly |
GB201702384D0 (en) * | 2017-02-14 | 2017-03-29 | Rolls Royce Plc | Gas turbine engine fan blade |
GB201702382D0 (en) * | 2017-02-14 | 2017-03-29 | Rolls Royce Plc | Gas turbine engine fan blade |
US11396888B1 (en) | 2017-11-09 | 2022-07-26 | Williams International Co., L.L.C. | System and method for guiding compressible gas flowing through a duct |
US11280199B2 (en) | 2018-11-21 | 2022-03-22 | Honeywell International Inc. | Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution |
GB201820423D0 (en) * | 2018-12-14 | 2019-01-30 | Rolls Royce Plc | Super-cooled ice impact protection for a gas turbine engine |
US11286779B2 (en) | 2020-06-03 | 2022-03-29 | Honeywell International Inc. | Characteristic distribution for rotor blade of booster rotor |
CN112211853B (zh) * | 2020-12-07 | 2021-02-12 | 中国航发上海商用航空发动机制造有限责任公司 | 压气机静子缘板前缘构型方法和相应的静子缘板 |
Family Cites Families (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2663493A (en) | 1949-04-26 | 1953-12-22 | A V Roe Canada Ltd | Blading for compressors, turbines, and the like |
US2746672A (en) | 1950-07-27 | 1956-05-22 | United Aircraft Corp | Compressor blading |
DE1903642A1 (de) | 1969-01-20 | 1970-08-06 | Bbc Sulzer Turbomaschinen | Schaufelung fuer Rotoren von Axialverdichtern |
US4358246A (en) * | 1979-07-16 | 1982-11-09 | United Technologies Corporation | Noise reduction means for prop-fan and the construction thereof |
GB2129882B (en) * | 1982-11-10 | 1986-04-16 | Rolls Royce | Gas turbine stator vane |
FR2556409B1 (fr) | 1983-12-12 | 1991-07-12 | Gen Electric | Aube perfectionnee pour moteur a turbine a gaz et procede de fabrication |
US4741667A (en) | 1986-05-28 | 1988-05-03 | United Technologies Corporation | Stator vane |
US5088892A (en) | 1990-02-07 | 1992-02-18 | United Technologies Corporation | Bowed airfoil for the compression section of a rotary machine |
US5167489A (en) | 1991-04-15 | 1992-12-01 | General Electric Company | Forward swept rotor blade |
US5211533A (en) | 1991-10-30 | 1993-05-18 | General Electric Company | Flow diverter for turbomachinery seals |
DE4228879A1 (de) | 1992-08-29 | 1994-03-03 | Asea Brown Boveri | Axialdurchströmte Turbine |
JPH0681603A (ja) * | 1992-09-03 | 1994-03-22 | Hitachi Ltd | 軸流形ターボ機械の静翼構造 |
US5642985A (en) | 1995-11-17 | 1997-07-01 | United Technologies Corporation | Swept turbomachinery blade |
GB9607316D0 (en) | 1996-04-09 | 1996-06-12 | Rolls Royce Plc | Swept fan blade |
US6071077A (en) | 1996-04-09 | 2000-06-06 | Rolls-Royce Plc | Swept fan blade |
US6077036A (en) * | 1998-08-20 | 2000-06-20 | General Electric Company | Bowed nozzle vane with selective TBC |
US6290465B1 (en) * | 1999-07-30 | 2001-09-18 | General Electric Company | Rotor blade |
FR2797658B1 (fr) | 1999-08-18 | 2002-08-23 | Snecma | Aube de turbine a profil ameliore |
US6312219B1 (en) | 1999-11-05 | 2001-11-06 | General Electric Company | Narrow waist vane |
US6299412B1 (en) | 1999-12-06 | 2001-10-09 | General Electric Company | Bowed compressor airfoil |
US6331100B1 (en) | 1999-12-06 | 2001-12-18 | General Electric Company | Doubled bowed compressor airfoil |
US6328533B1 (en) | 1999-12-21 | 2001-12-11 | General Electric Company | Swept barrel airfoil |
US6508630B2 (en) | 2001-03-30 | 2003-01-21 | General Electric Company | Twisted stator vane |
US6755612B2 (en) | 2002-09-03 | 2004-06-29 | Rolls-Royce Plc | Guide vane for a gas turbine engine |
FR2853022B1 (fr) | 2003-03-27 | 2006-07-28 | Snecma Moteurs | Aube de redresseur a double courbure |
US6899526B2 (en) | 2003-08-05 | 2005-05-31 | General Electric Company | Counterstagger compressor airfoil |
US7204676B2 (en) * | 2004-05-14 | 2007-04-17 | Pratt & Whitney Canada Corp. | Fan blade curvature distribution for high core pressure ratio fan |
US8292574B2 (en) | 2006-11-30 | 2012-10-23 | General Electric Company | Advanced booster system |
-
2006
- 2006-11-30 US US11/606,728 patent/US8087884B2/en active Active
-
2007
- 2007-11-15 CA CA2610541A patent/CA2610541C/en not_active Expired - Fee Related
- 2007-11-27 EP EP07121586.7A patent/EP1930600B1/en not_active Expired - Fee Related
- 2007-11-28 JP JP2007307216A patent/JP5410014B2/ja not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
CA2610541A1 (en) | 2008-05-30 |
EP1930600A3 (en) | 2010-05-26 |
CA2610541C (en) | 2015-06-30 |
EP1930600B1 (en) | 2014-09-24 |
EP1930600A2 (en) | 2008-06-11 |
JP2008138677A (ja) | 2008-06-19 |
US8087884B2 (en) | 2012-01-03 |
US20080131271A1 (en) | 2008-06-05 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP5410014B2 (ja) | 最新式ブースタステータベーン | |
JP5386076B2 (ja) | 最新式ブースタシステム | |
JP5419339B2 (ja) | 最新式ブースタロータブレード | |
US8464426B2 (en) | Gas turbine engine airfoil | |
US9726021B2 (en) | High order shaped curve region for an airfoil | |
JP6060145B2 (ja) | 高キャンバ圧縮機ロータブレード | |
KR102196815B1 (ko) | 베인을 갖는 반경류 또는 혼류 압축기 디퓨저 | |
JP2016109124A (ja) | 漏洩流を制御するための軸流圧縮機端壁処理部 | |
US20210372288A1 (en) | Compressor stator with leading edge fillet | |
RU2794951C2 (ru) | Лопатка газотурбинного двигателя с правилом максимальной толщины с большим запасом прочности при флаттере | |
KR102376903B1 (ko) | 블레이드와 이를 포함하는 압축기 및 가스 터빈 | |
US10935041B2 (en) | Pressure recovery axial-compressor blading |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20101119 |
|
RD04 | Notification of resignation of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7424 Effective date: 20101119 |
|
A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20120928 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20121002 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20121226 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20130104 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20130402 |
|
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20131008 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20131106 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
LAPS | Cancellation because of no payment of annual fees |