MX363296B - Pala de compresor para motor de turbina de gas. - Google Patents
Pala de compresor para motor de turbina de gas.Info
- Publication number
- MX363296B MX363296B MX2015007545A MX2015007545A MX363296B MX 363296 B MX363296 B MX 363296B MX 2015007545 A MX2015007545 A MX 2015007545A MX 2015007545 A MX2015007545 A MX 2015007545A MX 363296 B MX363296 B MX 363296B
- Authority
- MX
- Mexico
- Prior art keywords
- gas turbine
- turbine engine
- compressor blade
- root
- tip
- Prior art date
Links
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
-
- 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)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Se describe una pala de compresor (114) para un motor de turbina de gas (100). La pala de compresor puede incluir un origen (214), configurado de modo de emplear un centro (116) del motor de turbina de gas, y un perfil aerodinámico (218), que se extiende de manera axial desde el origen hasta una punta (222). El perfil aerodinámico puede tener una cara de succión, una cara de presión, un borde de ataque, que conecta las caras de succión y presión, y un borde de fuga, que conecta las caras de succión y presión opuestas al borde de ataque. A lo largo de su extensión desde el origen, el perfil aerodinámico puede dividirse en una pluralidad de regiones radialmente adyacentes (302, 304, 306, 308). Es posible que al menos una de las regiones radialmente adyacentes desde la base hasta la punta, aunque no todas ellas, tenga un espesor sustancialmente uniforme.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/720,640 US9506347B2 (en) | 2012-12-19 | 2012-12-19 | Compressor blade for gas turbine engine |
PCT/US2013/074268 WO2014099520A1 (en) | 2012-12-19 | 2013-12-11 | Compressor blade for gas turbine engine |
Publications (2)
Publication Number | Publication Date |
---|---|
MX2015007545A MX2015007545A (es) | 2015-09-25 |
MX363296B true MX363296B (es) | 2019-03-15 |
Family
ID=50929332
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
MX2015007545A MX363296B (es) | 2012-12-19 | 2013-12-11 | Pala de compresor para motor de turbina de gas. |
Country Status (5)
Country | Link |
---|---|
US (1) | US9506347B2 (es) |
CN (1) | CN104956032B (es) |
GB (1) | GB2523961B (es) |
MX (1) | MX363296B (es) |
WO (1) | WO2014099520A1 (es) |
Families Citing this family (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10982551B1 (en) | 2012-09-14 | 2021-04-20 | Raytheon Technologies Corporation | Turbomachine blade |
US9581170B2 (en) * | 2013-03-15 | 2017-02-28 | Honeywell International Inc. | Methods of designing and making diffuser vanes in a centrifugal compressor |
EP2971565B1 (en) * | 2013-03-15 | 2024-09-04 | RTX Corporation | Airfoil with thickened root and fan and engine incorporating same |
JP6364363B2 (ja) * | 2015-02-23 | 2018-07-25 | 三菱日立パワーシステムズ株式会社 | 2軸式ガスタービン及びその制御装置と制御方法 |
EP3081751B1 (en) * | 2015-04-14 | 2020-10-21 | Ansaldo Energia Switzerland AG | Cooled airfoil and method for manufacturing said airfoil |
FR3040071B1 (fr) * | 2015-08-11 | 2020-03-27 | Safran Aircraft Engines | Aube de rotor de turbomachine |
US10415591B2 (en) | 2016-09-21 | 2019-09-17 | United Technologies Corporation | Gas turbine engine airfoil |
US10865809B1 (en) * | 2017-01-17 | 2020-12-15 | Raytheon Technologies Corporation | Gas turbine engine airfoil frequency design |
US10808544B1 (en) * | 2017-01-17 | 2020-10-20 | Raytheon Technologies Corporation | Gas turbine engine airfoil frequency design |
US10844727B1 (en) * | 2017-01-17 | 2020-11-24 | Raytheon Technologies Corporation | Gas turbine engine airfoil frequency design |
US11199096B1 (en) | 2017-01-17 | 2021-12-14 | Raytheon Technologies Corporation | Turbomachine blade |
US11261737B1 (en) | 2017-01-17 | 2022-03-01 | Raytheon Technologies Corporation | Turbomachine blade |
GB201702380D0 (en) * | 2017-02-14 | 2017-03-29 | Rolls Royce Plc | Gas turbine engine fan blade with axial lean |
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 |
GB201702698D0 (en) * | 2017-02-20 | 2017-04-05 | Rolls Royce Plc | Fan |
US10801325B2 (en) * | 2017-03-27 | 2020-10-13 | Raytheon Technologies Corporation | Turbine blade with tip vortex control and tip shelf |
DE102017216620A1 (de) * | 2017-09-20 | 2019-03-21 | MTU Aero Engines AG | Schaufel für eine Strömungsmaschine |
EP3511522A1 (en) | 2018-01-11 | 2019-07-17 | Siemens Aktiengesellschaft | Gas turbine blade and method for producing such blade |
US10907479B2 (en) * | 2018-05-07 | 2021-02-02 | Raytheon Technologies Corporation | Airfoil having improved leading edge cooling scheme and damage resistance |
GB201813666D0 (en) * | 2018-08-22 | 2018-10-03 | Rolls Royce Plc | Fan blade |
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 |
US11421702B2 (en) | 2019-08-21 | 2022-08-23 | Pratt & Whitney Canada Corp. | Impeller with chordwise vane thickness variation |
FR3101108B1 (fr) * | 2019-09-24 | 2022-09-02 | Safran Helicopter Engines | Aube, notamment de turbomachine, partiellement recouverte en pied d’aube d’une bande de protection contre l’oxydation et la corrosion |
IT202000005146A1 (it) * | 2020-03-11 | 2021-09-11 | Ge Avio Srl | Motore a turbina con profilo aerodinamico avente alta accelerazione e bassa curva di paletta |
US20210381385A1 (en) * | 2020-06-03 | 2021-12-09 | Honeywell International Inc. | Characteristic distribution for rotor blade of booster rotor |
GB202216273D0 (en) * | 2022-11-02 | 2022-12-14 | Rolls Royce Plc | Fan blade for a gas turbine engine |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US857945A (en) * | 1906-06-15 | 1907-06-25 | Samuel D Latty | Juvenile hand-car. |
JPH08284884A (ja) | 1995-04-17 | 1996-10-29 | Mitsubishi Heavy Ind Ltd | 流体機械 |
JP2002048095A (ja) | 2000-08-03 | 2002-02-15 | Hitachi Ltd | 軸流圧縮機の翼 |
GB2381298A (en) | 2001-10-26 | 2003-04-30 | Rolls Royce Plc | A turbine blade having a greater thickness to chord ratio |
US7497664B2 (en) * | 2005-08-16 | 2009-03-03 | General Electric Company | Methods and apparatus for reducing vibrations induced to airfoils |
ITMI20060340A1 (it) | 2006-02-27 | 2007-08-28 | Nuovo Pignone Spa | Pala di un rotore di un secondo stadio di un compressore |
US8057188B2 (en) * | 2008-05-21 | 2011-11-15 | Alstom Technologies Ltd. Llc | Compressor airfoil |
US8167572B2 (en) | 2008-07-14 | 2012-05-01 | Pratt & Whitney Canada Corp. | Dynamically tuned turbine blade growth pocket |
US8147207B2 (en) | 2008-09-04 | 2012-04-03 | Siemens Energy, Inc. | Compressor blade having a ratio of leading edge sweep to leading edge dihedral in a range of 1:1 to 3:1 along the radially outer portion |
EP2241761A1 (en) * | 2009-04-09 | 2010-10-20 | Alstom Technology Ltd | Blade for an Axial Compressor and Manufacturing Method Thereof |
US8573945B2 (en) | 2009-11-13 | 2013-11-05 | Alstom Technology Ltd. | Compressor stator vane |
JP5305460B2 (ja) | 2009-12-11 | 2013-10-02 | 株式会社日立製作所 | 軸流送風機 |
US8596986B2 (en) * | 2011-02-23 | 2013-12-03 | Alstom Technology Ltd. | Unflared compressor blade |
-
2012
- 2012-12-19 US US13/720,640 patent/US9506347B2/en active Active
-
2013
- 2013-12-11 GB GB1512319.3A patent/GB2523961B/en active Active
- 2013-12-11 WO PCT/US2013/074268 patent/WO2014099520A1/en active Application Filing
- 2013-12-11 CN CN201380065240.3A patent/CN104956032B/zh active Active
- 2013-12-11 MX MX2015007545A patent/MX363296B/es unknown
Also Published As
Publication number | Publication date |
---|---|
GB2523961A (en) | 2015-09-09 |
CN104956032A (zh) | 2015-09-30 |
US20140165592A1 (en) | 2014-06-19 |
MX2015007545A (es) | 2015-09-25 |
GB2523961B (en) | 2020-02-19 |
CN104956032B (zh) | 2016-12-28 |
WO2014099520A1 (en) | 2014-06-26 |
GB201512319D0 (en) | 2015-08-19 |
US9506347B2 (en) | 2016-11-29 |
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