JP2015036544A - ターボ機械エアフォイル位置決め - Google Patents
ターボ機械エアフォイル位置決め Download PDFInfo
- Publication number
- JP2015036544A JP2015036544A JP2014157284A JP2014157284A JP2015036544A JP 2015036544 A JP2015036544 A JP 2015036544A JP 2014157284 A JP2014157284 A JP 2014157284A JP 2014157284 A JP2014157284 A JP 2014157284A JP 2015036544 A JP2015036544 A JP 2015036544A
- Authority
- JP
- Japan
- Prior art keywords
- airfoil
- turbomachine
- row
- diffuser
- airfoil row
- 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
- 238000000034 method Methods 0.000 claims description 31
- 239000012530 fluid Substances 0.000 claims description 11
- 230000001747 exhibiting effect Effects 0.000 claims 1
- 238000011144 upstream manufacturing Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
-
- 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
-
- 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
-
- 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
- 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
- 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
- F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
【解決手段】一実施形態は、ディフューザと、(1)前記ディフューザに隣接していて、静翼及び動翼より成る群から選択された第1の種類より成る第1のエアフォイル列、(2)前記第1のエアフォイル列に隣接していて、前記第1の種類とは異なる第2の種類より成る第2のエアフォイル列、及び(3)前記第2のエアフォイル列に隣接していて、前記第1の種類より成る第3のエアフォイル列を含んでいる複数のエアフォイル列とを有するターボ機械を含み、前記複数のエアフォイル列の内の少なくとも1つのエアフォイル列が、前記ターボ機械の別のエアフォイル列に対してクロックされて、ターボ機械の運転状態中に前記第1のエアフォイル列に隣接した前記ディフューザ内の少なくとも1つのスパン方向位置における空気流の円周方向圧力の変動を低減する。
【選択図】図1
Description
P ピッチ
S スパン
C1 内周
C2 外周
10、12、30 静翼
110、120、130、140、150、160 エアフォイル列
180ディフューザ
182 最小圧力
184 平均圧力
186 最大圧力
190 クロッキング前
192 クロッキング後
Claims (20)
- ディフューザと複数のエアフォイル列とを有するターボ機械であって、
前記複数のエアフォイル列は、
(1)前記ディフューザに隣接した第1のエアフォイル列であって、静翼及び動翼より成る群から選択された第1の種類より成る第1のエアフォイル列と、
(2)前記第1のエアフォイル列に隣接した第2のエアフォイル列であって、前記第1の種類とは異なる第2の種類より成る第2のエアフォイル列と、
(3)前記第2のエアフォイル列に隣接していて、前記第1の種類より成る第3のエアフォイル列とを含んでおり、
前記複数のエアフォイル列の内の少なくとも1つのエアフォイル列が、前記ターボ機械の別のエアフォイル列に対してクロックされて、前記ターボ機械の運転状態中に前記第1のエアフォイル列に隣接した前記ディフューザ内の少なくとも1つのスパン方向位置における空気流の円周方向圧力の変動を低減すること、
を特徴とするターボ機械。 - タービン、エンジン及び圧縮機より成る群から選択された請求項1記載のターボ機械。
- 前記ターボ機械はガスタービンである、請求項2記載のターボ機械。
- 前記複数のエアフォイル列の内の少なくとも1つのエアフォイル列は、前記ディフューザの表面上の少なくとも1つの点における空気流圧力の第1の変動を示す第1の相対的位置であって、第2の相対的位置で示される前記ディフューザ内の少なくとも1つの点における空気流圧力の第2の変動よりも小さい該第1の変動を示す第1の相対的位置にクロックされる、請求項1記載のターボ機械。
- 前記第1及び第2の変動は、前記ターボ機械の前記少なくとも1つのエアフォイル列及び別のエアフォイル列の相対的位置を用いて計算される、請求項4記載のターボ機械。
- 前記第1及び第2の変動は、計算流体力学方程式を用いて計算される、請求項5記載のターボ機械。
- 前記計算流体力学方程式はナビエ−ストークス方程式を含んでいる、請求項6記載のターボ機械。
- クロックされる前記複数のエアフォイル列の内の前記少なくとも1つのエアフォイル列は、前記第3のエアフォイル列を含んでいる、請求項1記載のターボ機械。
- 前記第1及び第3のエアフォイル列は動翼列であり、また前記第2のエアフォイル列は静翼列である、請求項9記載のターボ機械。
- ターボ機械のディフューザに入る空気流圧力の変動を低減する方法であって、
前記ターボ機械の少なくとも3つのエアフォイル列を横切る空気流を計算する段階であって、前記少なくとも3つのエアフォイル列が、(1)前記ターボ機械の前記ディフューザに隣接していて、静翼及び動翼より成る群から選択された第1の種類より成る第1のエアフォイル列、(2)前記第1のエアフォイル列に隣接していて、前記第1の種類とは異なる第2の種類より成る第2のエアフォイル列、及び(3)前記第2のエアフォイル列に隣接していて、前記第1の種類より成る第3のエアフォイル列を含んでいる、段階と、
前記ディフューザの少なくとも1つのスパン方向位置における圧力変動を評価する段階と、
前記圧力変動が所定の目標内にあるかどうか決定する段階と、
有する方法。 - 前記圧力変動が前記所定の目標内に無い場合、前記方法は、更に、
前記少なくとも3つのエアフォイル列の内の少なくとも1つのエアフォイル列の相対的クロッキング位置を変更する段階と、
前記少なくとも3つのエアフォイル列を横切る空気流を再計算する段階と、
前記ディフューザの前記少なくとも1つのスパン方向位置における圧力変動を再評価する段階と、
前記再評価された圧力変動が前記所定の目標内にあるかどうか決定する段階と、
を有している、請求項11記載の方法。 - 前記相対的クロッキング位置を変更する前記段階は、前記第1、第2又は第3のエアフォイル列以外のエアフォイル列のクロッキング位置を変更する段階を含んでいる、請求項11記載の方法。
- 前記空気流を計算する前記段階は、計算流体力学方程式を用いることを含んでいる、請求項10記載の方法。
- 前記計算流体力学方程式はナビエ−ストークス・ソルバー方程式を含んでいる、請求項13記載の方法。
- (欠番)
- ターボ機械のディフューザに入る空気流圧力の変動を低減する方法であって、
前記ターボ機械の少なくとも3つのエアフォイル列を横切る空気流を計算する段階と、
前記ターボ機械のディフューザの少なくとも1つのスパン方向位置における第1の圧力変動を評価する段階と、
前記3つのエアフォイル列の内の少なくとも1つのエアフォイル列の相対的クロッキング位置を変更する段階と、
前記少なくとも3つのエアフォイル列を横切る空気流を再計算する段階と、
前記ディフューザの前記少なくとも1つのスパン方向位置における第2の圧力変動を評価する段階と、
前記第2の圧力変動が前記第1の圧力変動よりも小さいかどうか決定する段階と、
前記第2の圧力変動が前記第1の圧力変動よりも小さい場合に、前記少なくとも1つのエアフォイル列の前記変更した相対的クロッキング位置を使用して前記ターボ機械を運転する段階と、
を有する方法。 - 前記少なくとも3つのエアフォイル列が、(1)前記ターボ機械の前記ディフューザに隣接していて、静翼及び動翼より成る群から選択された第1の種類より成る第1のエアフォイル列、(2)前記第1のエアフォイル列に隣接していて、前記第1の種類とは異なる第2の種類より成る第2のエアフォイル列、及び(3)前記第2のエアフォイル列に隣接していて、前記第1の種類より成る第3のエアフォイル列を含んでいる、請求項16記載の方法。
- 前記相対的クロッキング位置を変更する前記段階は、前記第1、第2又は第3のエアフォイル列以外のエアフォイル列のクロッキング位置を変更する段階を含んでいる、請求項17記載の方法。
- 前記空気流を計算する前記段階は、計算流体力学方程式を用いることを含んでいる、請求項16記載の方法。
- 前記計算流体力学方程式はナビエ−ストークス・ソルバー方程式を含んでいる、請求項19記載の方法。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/963,689 US9435221B2 (en) | 2013-08-09 | 2013-08-09 | Turbomachine airfoil positioning |
US13/963,689 | 2013-08-09 |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2015036544A true JP2015036544A (ja) | 2015-02-23 |
JP2015036544A5 JP2015036544A5 (ja) | 2017-09-07 |
JP6514455B2 JP6514455B2 (ja) | 2019-05-15 |
Family
ID=52388949
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2014157284A Active JP6514455B2 (ja) | 2013-08-09 | 2014-08-01 | ターボ機械エアフォイル位置決め |
Country Status (5)
Country | Link |
---|---|
US (1) | US9435221B2 (ja) |
JP (1) | JP6514455B2 (ja) |
CN (1) | CN105019949B (ja) |
CH (1) | CH708447A2 (ja) |
DE (1) | DE102014110315A1 (ja) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102014204346A1 (de) * | 2014-03-10 | 2015-09-10 | Rolls-Royce Deutschland Ltd & Co Kg | Verfahren zur Herstellung eines doppelreihigen Schaufelrads für eine Strömungsmaschine und doppelreihiges Schaufelrad |
US20160177835A1 (en) * | 2014-12-22 | 2016-06-23 | Pratt & Whitney Canada Corp. | Gas turbine engine with angularly offset turbine vanes |
FR3044412B1 (fr) * | 2015-11-30 | 2018-11-09 | Safran Aircraft Engines | Veine instrumentee de turbomachine |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2005220797A (ja) * | 2004-02-05 | 2005-08-18 | Mitsubishi Heavy Ind Ltd | タービン |
JP2006138250A (ja) * | 2004-11-11 | 2006-06-01 | Mitsubishi Heavy Ind Ltd | 軸流形回転流体機械 |
US20100011684A1 (en) * | 2005-02-03 | 2010-01-21 | Guardian, Llc | Window Framing System for Sliding Windows |
JP2010156339A (ja) * | 2008-12-29 | 2010-07-15 | General Electric Co <Ge> | タービンエーロフォイルのクロッキング |
JP2011241791A (ja) * | 2010-05-20 | 2011-12-01 | Kawasaki Heavy Ind Ltd | ガスタービンエンジンのタービン |
Family Cites Families (120)
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 |
US3347520A (en) | 1966-07-12 | 1967-10-17 | Jerzy A Oweczarek | Turbomachine blading |
US3734639A (en) | 1968-01-25 | 1973-05-22 | Gen Motors Corp | Turbine cooling |
US3572962A (en) | 1969-06-02 | 1971-03-30 | Canadian Patents Dev | Stator blading for noise reduction in turbomachinery |
SE343106B (ja) | 1969-06-30 | 1972-02-28 | E Janelid | |
US3745629A (en) | 1972-04-12 | 1973-07-17 | Secr Defence | Method of determining optimal shapes for stator blades |
PL111037B1 (en) | 1975-11-03 | 1980-08-30 | Working blade,especially long one,for steam and gas turbines and axial compressors | |
JPS54114619A (en) | 1978-02-28 | 1979-09-06 | Toshiba Corp | Natural frequency adjusting method of turbine blade |
JPS54114618A (en) | 1978-02-28 | 1979-09-06 | Toshiba Corp | Moving and stator blades arranging method of turbine |
US4259842A (en) | 1978-12-11 | 1981-04-07 | General Electric Company | Combustor liner slot with cooled props |
GB2129882B (en) | 1982-11-10 | 1986-04-16 | Rolls Royce | Gas turbine stator vane |
US4619580A (en) | 1983-09-08 | 1986-10-28 | The Boeing Company | Variable camber vane and method therefor |
US4585395A (en) | 1983-12-12 | 1986-04-29 | General Electric Company | Gas turbine engine blade |
US4616975A (en) | 1984-07-30 | 1986-10-14 | General Electric Company | Diaphragm for a steam turbine |
GB2164098B (en) | 1984-09-07 | 1988-12-07 | Rolls Royce | Improvements in or relating to aerofoil section members for turbine engines |
US4968216A (en) | 1984-10-12 | 1990-11-06 | The Boeing Company | Two-stage fluid driven turbine |
CA1324999C (en) | 1986-04-30 | 1993-12-07 | Walter M. Presz, Jr. | Bodies with reduced surface drag |
GB2192229B (en) | 1986-07-04 | 1990-05-02 | Rolls Royce Plc | A compressor and air bleed system |
CH672004A5 (ja) | 1986-09-26 | 1989-10-13 | Bbc Brown Boveri & Cie | |
US4896510A (en) | 1987-02-06 | 1990-01-30 | General Electric Company | Combustor liner cooling arrangement |
GB2207191B (en) | 1987-07-06 | 1992-03-04 | Gen Electric | Gas turbine engine |
JP2753382B2 (ja) | 1990-09-17 | 1998-05-20 | 株式会社日立製作所 | 軸流タービン静翼装置及び軸流タービン |
DE59010740D1 (de) | 1990-12-05 | 1997-09-04 | Asea Brown Boveri | Gasturbinen-Brennkammer |
US5274991A (en) | 1992-03-30 | 1994-01-04 | General Electric Company | Dry low NOx multi-nozzle combustion liner cap assembly |
DE4228879A1 (de) | 1992-08-29 | 1994-03-03 | Asea Brown Boveri | Axialdurchströmte Turbine |
US5406786A (en) | 1993-07-16 | 1995-04-18 | Air Products And Chemicals, Inc. | Integrated air separation - gas turbine electrical generation process |
US5749218A (en) | 1993-12-17 | 1998-05-12 | General Electric Co. | Wear reduction kit for gas turbine combustors |
US5486091A (en) | 1994-04-19 | 1996-01-23 | United Technologies Corporation | Gas turbine airfoil clocking |
GB2293631B (en) | 1994-09-30 | 1998-09-09 | Gen Electric | Composite fan blade trailing edge reinforcement |
US6170264B1 (en) | 1997-09-22 | 2001-01-09 | Clean Energy Systems, Inc. | Hydrocarbon combustion power generation system with CO2 sequestration |
GB2311596B (en) | 1996-03-29 | 2000-07-12 | Europ Gas Turbines Ltd | Combustor for gas - or liquid - fuelled turbine |
US5813828A (en) | 1997-03-18 | 1998-09-29 | Norris; Thomas R. | Method and apparatus for enhancing gas turbo machinery flow |
EP0936406B1 (en) | 1998-02-10 | 2004-05-06 | General Electric Company | Burner with uniform fuel/air premixing for low emissions combustion |
FR2775288B1 (fr) | 1998-02-26 | 2000-03-31 | Rhone Poulenc Rorer Sa | Derives de streptogramines, leur preparation et les compositons qui les contiennent |
WO1999064725A1 (en) | 1998-06-12 | 1999-12-16 | Ebara Corporation | Turbine nozzle vane |
US6626635B1 (en) | 1998-09-30 | 2003-09-30 | General Electric Company | System for controlling clearance between blade tips and a surrounding casing in rotating machinery |
US6174129B1 (en) | 1999-01-07 | 2001-01-16 | Siemens Westinghouse Power Corporation | Turbine vane clocking mechanism and method of assembling a turbine having such a mechanism |
US6345493B1 (en) | 1999-06-04 | 2002-02-12 | Air Products And Chemicals, Inc. | Air separation process and system with gas turbine drivers |
FR2797658B1 (fr) | 1999-08-18 | 2002-08-23 | Snecma | Aube de turbine a profil ameliore |
US6484505B1 (en) | 2000-02-25 | 2002-11-26 | General Electric Company | Combustor liner cooling thimbles and related method |
GB2359882B (en) | 2000-02-29 | 2004-01-07 | Rolls Royce Plc | Wall elements for gas turbine engine combustors |
US6389793B1 (en) | 2000-04-19 | 2002-05-21 | General Electric Company | Combustion turbine cooling media supply system and related method |
US6824710B2 (en) | 2000-05-12 | 2004-11-30 | Clean Energy Systems, Inc. | Working fluid compositions for use in semi-closed brayton cycle gas turbine power systems |
US6435814B1 (en) | 2000-05-16 | 2002-08-20 | General Electric Company | Film cooling air pocket in a closed loop cooled airfoil |
US6446438B1 (en) | 2000-06-28 | 2002-09-10 | Power Systems Mfg., Llc | Combustion chamber/venturi cooling for a low NOx emission combustor |
US6602458B1 (en) | 2000-06-28 | 2003-08-05 | Rubbermaid Incorporated | Reduced flash molding |
US6402458B1 (en) * | 2000-08-16 | 2002-06-11 | General Electric Company | Clock turbine airfoil cooling |
US6442941B1 (en) | 2000-09-11 | 2002-09-03 | General Electric Company | Compressor discharge bleed air circuit in gas turbine plants and related method |
IT1320722B1 (it) | 2000-10-23 | 2003-12-10 | Fiatavio Spa | Metodo per il posizionamento di schiere di stadi di una turbina,particolarmente per motori aeronautici. |
DE10053361C1 (de) | 2000-10-27 | 2002-06-06 | Mtu Aero Engines Gmbh | Schaufelgitteranordnung für Turbomaschinen |
US6409126B1 (en) | 2000-11-01 | 2002-06-25 | Lockhead Martin Corporation | Passive flow control of bluff body wake turbulence |
JP2002213206A (ja) | 2001-01-12 | 2002-07-31 | Mitsubishi Heavy Ind Ltd | ガスタービンにおける翼構造 |
GB2373319B (en) | 2001-03-12 | 2005-03-30 | Rolls Royce Plc | Combustion apparatus |
DE10115947C2 (de) | 2001-03-30 | 2003-02-27 | Deutsch Zentr Luft & Raumfahrt | Verfahren zur Relativpositionierung von aufeinander folgenden Statoren oder Rotoren einer transsonischen Hochdruckturbine |
US6554562B2 (en) | 2001-06-15 | 2003-04-29 | Honeywell International, Inc. | Combustor hot streak alignment for gas turbine engine |
JP4786077B2 (ja) | 2001-08-10 | 2011-10-05 | 本田技研工業株式会社 | タービン用静翼及びその製造方法 |
FR2835019B1 (fr) | 2002-01-22 | 2004-12-31 | Snecma Moteurs | Diffuseur pour moteur a turbine a gaz terrestre ou aeronautique |
JP2004011458A (ja) * | 2002-06-04 | 2004-01-15 | Ishikawajima Harima Heavy Ind Co Ltd | 静翼クロッキング装置とその位置制御方法 |
US6772595B2 (en) | 2002-06-25 | 2004-08-10 | Power Systems Mfg., Llc | Advanced cooling configuration for a low emissions combustor venturi |
USD511377S1 (en) | 2002-07-01 | 2005-11-08 | Donaldson Company, Inc. | Inlet air filter hood module for gas turbine systems |
JP3927887B2 (ja) | 2002-08-09 | 2007-06-13 | 本田技研工業株式会社 | 軸流圧縮機の静翼 |
US6926345B2 (en) | 2002-09-20 | 2005-08-09 | The Regents Of The University Of California | Apparatus and method for reducing drag of a bluff body in ground effect using counter-rotating vortex pairs |
US6899081B2 (en) | 2002-09-20 | 2005-05-31 | Visteon Global Technologies, Inc. | Flow conditioning device |
US20040109756A1 (en) | 2002-12-09 | 2004-06-10 | Mitsubishi Heavy Industries Ltd. | Gas turbine |
FR2853022B1 (fr) | 2003-03-27 | 2006-07-28 | Snecma Moteurs | Aube de redresseur a double courbure |
US6935116B2 (en) | 2003-04-28 | 2005-08-30 | Power Systems Mfg., Llc | Flamesheet combustor |
US6866479B2 (en) | 2003-05-16 | 2005-03-15 | Mitsubishi Heavy Industries, Ltd. | Exhaust diffuser for axial-flow turbine |
EP1482246A1 (de) | 2003-05-30 | 2004-12-01 | Siemens Aktiengesellschaft | Brennkammer |
JP4040556B2 (ja) | 2003-09-04 | 2008-01-30 | 株式会社日立製作所 | ガスタービン設備及び冷却空気供給方法 |
US6913441B2 (en) | 2003-09-04 | 2005-07-05 | Siemens Westinghouse Power Corporation | Turbine blade ring assembly and clocking method |
GB2407136B (en) | 2003-10-15 | 2007-10-03 | Alstom | Turbine rotor blade for gas turbine engine |
US7007478B2 (en) | 2004-06-30 | 2006-03-07 | General Electric Company | Multi-venturi tube fuel injector for a gas turbine combustor |
US7340129B2 (en) | 2004-08-04 | 2008-03-04 | Colorado State University Research Foundation | Fiber laser coupled optical spark delivery system |
US7412129B2 (en) | 2004-08-04 | 2008-08-12 | Colorado State University Research Foundation | Fiber coupled optical spark delivery system |
US7574865B2 (en) | 2004-11-18 | 2009-08-18 | Siemens Energy, Inc. | Combustor flow sleeve with optimized cooling and airflow distribution |
DE502005004938D1 (de) | 2005-05-10 | 2008-09-18 | Mtu Aero Engines Gmbh | Verfahren zur Strömungsoptimierung in mehrstufigen Turbomaschinen |
US7707835B2 (en) | 2005-06-15 | 2010-05-04 | General Electric Company | Axial flow sleeve for a turbine combustor and methods of introducing flow sleeve air |
US7588412B2 (en) | 2005-07-28 | 2009-09-15 | General Electric Company | Cooled shroud assembly and method of cooling a shroud |
ATE512876T1 (de) | 2005-10-17 | 2011-07-15 | Bell Helicopter Textron Inc | Plasmaaktuatoren zur widerstandsreduzierung auf flügeln, gondeln und/oder rumpf eines senkrecht startenden oder landenden flugzeugs |
CN100376765C (zh) | 2005-10-28 | 2008-03-26 | 中国科学院工程热物理研究所 | 一种用于多级叶轮机的三维时序效益最大化方法 |
US7805946B2 (en) | 2005-12-08 | 2010-10-05 | Siemens Energy, Inc. | Combustor flow sleeve attachment system |
US7762074B2 (en) | 2006-04-04 | 2010-07-27 | Siemens Energy, Inc. | Air flow conditioner for a combustor can of a gas turbine engine |
CN101050722A (zh) | 2006-04-07 | 2007-10-10 | 孙敏超 | 一种变出口流动截面涡轮喷嘴环 |
US7654320B2 (en) | 2006-04-07 | 2010-02-02 | Occidental Energy Ventures Corp. | System and method for processing a mixture of hydrocarbon and CO2 gas produced from a hydrocarbon reservoir |
US7681403B2 (en) | 2006-04-13 | 2010-03-23 | General Electric Company | Forward sleeve retainer plate and method |
US7758306B2 (en) | 2006-12-22 | 2010-07-20 | General Electric Company | Turbine assembly for a gas turbine engine and method of manufacturing the same |
FR2913074B1 (fr) | 2007-02-27 | 2009-05-22 | Snecma Sa | Methode de reduction des niveaux vibratoires d'une roue aubagee de turbomachine. |
US8117845B2 (en) | 2007-04-27 | 2012-02-21 | General Electric Company | Systems to facilitate reducing flashback/flame holding in combustion systems |
US7966820B2 (en) | 2007-08-15 | 2011-06-28 | General Electric Company | Method and apparatus for combusting fuel within a gas turbine engine |
CN100462566C (zh) | 2007-11-29 | 2009-02-18 | 北京航空航天大学 | 叶片沿周向非均匀分布的大小叶片叶轮及压气机 |
FR2925106B1 (fr) | 2007-12-14 | 2010-01-22 | Snecma | Procede de conception d'une turbine multi-etages de turbomachine |
US7896645B2 (en) | 2008-05-30 | 2011-03-01 | Universal Cleanair Technologies | Three phased combustion system |
US8540490B2 (en) | 2008-06-20 | 2013-09-24 | General Electric Company | Noise reduction in a turbomachine, and a related method thereof |
CH699309A1 (de) | 2008-08-14 | 2010-02-15 | Alstom Technology Ltd | Thermische maschine mit luftgekühlter, ringförmiger brennkammer. |
US20100054922A1 (en) * | 2008-09-04 | 2010-03-04 | General Electric Company | Turbine airfoil clocking |
US20100054929A1 (en) * | 2008-09-04 | 2010-03-04 | General Electric Company | Turbine airfoil clocking |
US8297919B2 (en) | 2008-10-31 | 2012-10-30 | General Electric Company | Turbine airfoil clocking |
US8087253B2 (en) | 2008-11-20 | 2012-01-03 | General Electric Company | Methods, apparatus and systems concerning the circumferential clocking of turbine airfoils in relation to combustor cans and the flow of cooling air through the turbine hot gas flowpath |
JP4923073B2 (ja) | 2009-02-25 | 2012-04-25 | 株式会社日立製作所 | 遷音速翼 |
US8307657B2 (en) | 2009-03-10 | 2012-11-13 | General Electric Company | Combustor liner cooling system |
JP5374199B2 (ja) | 2009-03-19 | 2013-12-25 | 三菱重工業株式会社 | ガスタービン |
US8234872B2 (en) | 2009-05-01 | 2012-08-07 | General Electric Company | Turbine air flow conditioner |
US8720206B2 (en) | 2009-05-14 | 2014-05-13 | General Electric Company | Methods and systems for inducing combustion dynamics |
US8650881B2 (en) | 2009-06-30 | 2014-02-18 | General Electric Company | Methods and apparatus for combustor fuel circuit for ultra low calorific fuels |
US8646276B2 (en) | 2009-11-11 | 2014-02-11 | General Electric Company | Combustor assembly for a turbine engine with enhanced cooling |
US8381526B2 (en) | 2010-02-15 | 2013-02-26 | General Electric Company | Systems and methods of providing high pressure air to a head end of a combustor |
US8516822B2 (en) | 2010-03-02 | 2013-08-27 | General Electric Company | Angled vanes in combustor flow sleeve |
US8684684B2 (en) | 2010-08-31 | 2014-04-01 | General Electric Company | Turbine assembly with end-wall-contoured airfoils and preferenttial clocking |
US8707672B2 (en) | 2010-09-10 | 2014-04-29 | General Electric Company | Apparatus and method for cooling a combustor cap |
US8991187B2 (en) | 2010-10-11 | 2015-03-31 | General Electric Company | Combustor with a lean pre-nozzle fuel injection system |
JP2012145098A (ja) | 2010-12-21 | 2012-08-02 | Toshiba Corp | トランジションピースおよびガスタービン |
US8991188B2 (en) | 2011-01-05 | 2015-03-31 | General Electric Company | Fuel nozzle passive purge cap flow |
US8850822B2 (en) | 2011-01-24 | 2014-10-07 | General Electric Company | System for pre-mixing in a fuel nozzle |
US8893501B2 (en) | 2011-03-28 | 2014-11-25 | General Eletric Company | Combustor crossfire tube |
US8919127B2 (en) | 2011-05-24 | 2014-12-30 | General Electric Company | System and method for flow control in gas turbine engine |
US20130081402A1 (en) * | 2011-10-03 | 2013-04-04 | General Electric Company | Turbomachine having a gas flow aeromechanic system and method |
US9115602B2 (en) | 2011-10-19 | 2015-08-25 | Siemens Aktiengesellschaft | Exhaust diffuser including flow mixing ramp for a gas turbine engine |
US8899975B2 (en) | 2011-11-04 | 2014-12-02 | General Electric Company | Combustor having wake air injection |
US9500085B2 (en) | 2012-07-23 | 2016-11-22 | General Electric Company | Method for modifying gas turbine performance |
US20140072433A1 (en) | 2012-09-10 | 2014-03-13 | General Electric Company | Method of clocking a turbine by reshaping the turbine's downstream airfoils |
-
2013
- 2013-08-09 US US13/963,689 patent/US9435221B2/en active Active
-
2014
- 2014-07-22 DE DE201410110315 patent/DE102014110315A1/de active Pending
- 2014-08-01 JP JP2014157284A patent/JP6514455B2/ja active Active
- 2014-08-07 CH CH01203/14A patent/CH708447A2/de not_active Application Discontinuation
- 2014-08-08 CN CN201410389920.7A patent/CN105019949B/zh active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2005220797A (ja) * | 2004-02-05 | 2005-08-18 | Mitsubishi Heavy Ind Ltd | タービン |
JP2006138250A (ja) * | 2004-11-11 | 2006-06-01 | Mitsubishi Heavy Ind Ltd | 軸流形回転流体機械 |
US20100011684A1 (en) * | 2005-02-03 | 2010-01-21 | Guardian, Llc | Window Framing System for Sliding Windows |
JP2010156339A (ja) * | 2008-12-29 | 2010-07-15 | General Electric Co <Ge> | タービンエーロフォイルのクロッキング |
JP2011241791A (ja) * | 2010-05-20 | 2011-12-01 | Kawasaki Heavy Ind Ltd | ガスタービンエンジンのタービン |
Also Published As
Publication number | Publication date |
---|---|
DE102014110315A1 (de) | 2015-02-12 |
CH708447A2 (de) | 2015-02-13 |
US9435221B2 (en) | 2016-09-06 |
CN105019949A (zh) | 2015-11-04 |
CN105019949B (zh) | 2018-06-05 |
JP6514455B2 (ja) | 2019-05-15 |
US20150044017A1 (en) | 2015-02-12 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
Lettieri et al. | Low-flow-coefficient centrifugal compressor design for supercritical CO2 | |
US8647054B2 (en) | Axial turbo engine with low gap losses | |
US8297919B2 (en) | Turbine airfoil clocking | |
JP5850968B2 (ja) | 不均一に分布させられた翼と均一なスロート面積とを備えたノズルリング | |
JP2010223010A (ja) | ガスタービン | |
CN109815624A (zh) | 一种考虑进气总压畸变影响的压气机稳定边界判断方法 | |
US10408070B2 (en) | Turbine engine guide vane | |
JP2016512586A5 (ja) | ||
Gunn et al. | Non-axisymmetric stator design for boundary layer ingesting fans | |
JP6514455B2 (ja) | ターボ機械エアフォイル位置決め | |
Lindemann et al. | Development of a new design method for high efficiency swept low pressure axial fans with small hub/tip ratio | |
CN110030038B (zh) | 考虑bli进气畸变效应的叶尖跨音风扇非对称静子设计方法 | |
US9500085B2 (en) | Method for modifying gas turbine performance | |
US9482237B1 (en) | Method of designing a multi-stage turbomachine compressor | |
Witteck et al. | Comparison of transient blade row methods for the CFD analysis of a high-pressure turbine | |
Stummann et al. | Circumferentially non-uniform flow in the rear stage of a multistage compressor | |
Kikuchi et al. | Detailed studies on aerodynamic performance and unsteady flow behaviors of a single turbine stage with variable rotor-stator axial gap | |
Tanuma | Design and analysis for aerodynamic efficiency enhancement of steam turbines | |
Marn et al. | The effect of rotor tip clearance size onto the separated flow through a super-aggressive s-shaped intermediate turbine duct downstream of a transonic turbine stage | |
CN103670526A (zh) | 通过再成形涡轮的下游翼型件对涡轮设置时序的方法 | |
JP2010059967A (ja) | タービン翼形部をクロッキングする方法 | |
Lesser et al. | Numerical investigation of a highly loaded axial compressor stage with inlet distortions | |
Gao et al. | Experimental investigation of effects of tip cavity on tip clearance flow in a variable-geometry turbine cascade | |
Gombert et al. | Unsteady aerodynamical blade row interaction in a new multistage research turbine: Part 1—experimental investigation | |
Kunte et al. | Experimental investigation of a truncated pipe diffuser with a tandem deswirler in a centrifugal compressor stage |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20170724 |
|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20170724 |
|
A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20180531 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20180605 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20180705 |
|
A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20181009 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20190129 |
|
A911 | Transfer to examiner for re-examination before appeal (zenchi) |
Free format text: JAPANESE INTERMEDIATE CODE: A911 Effective date: 20190205 |
|
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: 20190409 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20190412 |
|
R150 | Certificate of patent or registration of utility model |
Ref document number: 6514455 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
S111 | Request for change of ownership or part of ownership |
Free format text: JAPANESE INTERMEDIATE CODE: R313113 |
|
R360 | Written notification for declining of transfer of rights |
Free format text: JAPANESE INTERMEDIATE CODE: R360 |
|
R360 | Written notification for declining of transfer of rights |
Free format text: JAPANESE INTERMEDIATE CODE: R360 |
|
R371 | Transfer withdrawn |
Free format text: JAPANESE INTERMEDIATE CODE: R371 |
|
S111 | Request for change of ownership or part of ownership |
Free format text: JAPANESE INTERMEDIATE CODE: R313113 |
|
R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |