WO2012134833A3 - High camber compressor rotor blade - Google Patents

High camber compressor rotor blade Download PDF

Info

Publication number
WO2012134833A3
WO2012134833A3 PCT/US2012/029357 US2012029357W WO2012134833A3 WO 2012134833 A3 WO2012134833 A3 WO 2012134833A3 US 2012029357 W US2012029357 W US 2012029357W WO 2012134833 A3 WO2012134833 A3 WO 2012134833A3
Authority
WO
WIPO (PCT)
Prior art keywords
airfoil
height location
tip
rotor blade
root
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.)
Ceased
Application number
PCT/US2012/029357
Other languages
French (fr)
Other versions
WO2012134833A2 (en
Inventor
Brent Franklin BEACHER
David Scott Clark
Andrew Breeze-Stringfellow
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to EP12718449.7A priority Critical patent/EP2689138A2/en
Priority to CN201280015055.9A priority patent/CN103814192B/en
Priority to CA2830257A priority patent/CA2830257A1/en
Priority to JP2014501156A priority patent/JP6060145B2/en
Publication of WO2012134833A2 publication Critical patent/WO2012134833A2/en
Publication of WO2012134833A3 publication Critical patent/WO2012134833A3/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A rotor blade (104) having an airfoil (10) for a compressor is described. The airfoil has an airfoil root (11), an airfoil tip (12) located at a spanwise distance from the airfoil root, a leading edge (20) extending from the airfoil root to the airfoil tip, an inner span region (13, S2) between the airfoil root and a first height location (41) on the airfoil leading edge, a midspan region (23, S2) between the first height location and a second height location (42) on the airfoil leading edge located radially outward from the first height location; an outer span region (14, S3) between the second height location and the airfoil tip, wherein the airfoil has a normalized camber profile (120) such that the normalized camber increases in the outer span region in a spanwise direction towards the tip and is more than 2.2 in the outer span region.
PCT/US2012/029357 2011-03-25 2012-03-16 High camber compressor rotor blade Ceased WO2012134833A2 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP12718449.7A EP2689138A2 (en) 2011-03-25 2012-03-16 High camber compressor rotor blade
CN201280015055.9A CN103814192B (en) 2011-03-25 2012-03-16 high camber compressor rotor blade
CA2830257A CA2830257A1 (en) 2011-03-25 2012-03-16 High camber compressor rotor blade
JP2014501156A JP6060145B2 (en) 2011-03-25 2012-03-16 High camber compressor rotor blade

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/072,027 US8702398B2 (en) 2011-03-25 2011-03-25 High camber compressor rotor blade
US13/072,027 2011-03-25

Publications (2)

Publication Number Publication Date
WO2012134833A2 WO2012134833A2 (en) 2012-10-04
WO2012134833A3 true WO2012134833A3 (en) 2013-02-14

Family

ID=46025880

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2012/029357 Ceased WO2012134833A2 (en) 2011-03-25 2012-03-16 High camber compressor rotor blade

Country Status (6)

Country Link
US (1) US8702398B2 (en)
EP (1) EP2689138A2 (en)
JP (1) JP6060145B2 (en)
CN (1) CN103814192B (en)
CA (1) CA2830257A1 (en)
WO (1) WO2012134833A2 (en)

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US9017036B2 (en) 2012-02-29 2015-04-28 United Technologies Corporation High order shaped curve region for an airfoil
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FR3009588B1 (en) 2013-08-07 2018-01-26 Safran Aircraft Engines MOBILE AUB OF TURBOMACHINE
US9567858B2 (en) 2014-02-19 2017-02-14 United Technologies Corporation Gas turbine engine airfoil
EP3985226B1 (en) 2014-02-19 2024-12-25 RTX Corporation Gas turbine engine airfoil
US10584715B2 (en) 2014-02-19 2020-03-10 United Technologies Corporation Gas turbine engine airfoil
US10465702B2 (en) 2014-02-19 2019-11-05 United Technologies Corporation Gas turbine engine airfoil
EP3108106B1 (en) 2014-02-19 2022-05-04 Raytheon Technologies Corporation Gas turbine engine airfoil
WO2015175052A2 (en) 2014-02-19 2015-11-19 United Technologies Corporation Gas turbine engine airfoil
WO2015126941A1 (en) * 2014-02-19 2015-08-27 United Technologies Corporation Gas turbine engine airfoil
EP3575551B1 (en) 2014-02-19 2021-10-27 Raytheon Technologies Corporation Gas turbine engine airfoil
WO2015175044A2 (en) 2014-02-19 2015-11-19 United Technologies Corporation Gas turbine engine airfoil
EP3108123B1 (en) 2014-02-19 2023-10-04 Raytheon Technologies Corporation Turbofan engine with geared architecture and lpc airfoils
EP3108120B1 (en) 2014-02-19 2021-03-31 Raytheon Technologies Corporation Gas turbine engine having a geared architecture and a specific fixed airfoil structure
WO2015175043A2 (en) 2014-02-19 2015-11-19 United Technologies Corporation Gas turbine engine airfoil
EP3108105B1 (en) 2014-02-19 2021-05-12 Raytheon Technologies Corporation Gas turbine engine airfoil
WO2015126454A1 (en) 2014-02-19 2015-08-27 United Technologies Corporation Gas turbine engine airfoil
US10570916B2 (en) 2014-02-19 2020-02-25 United Technologies Corporation Gas turbine engine airfoil
WO2015175073A2 (en) 2014-02-19 2015-11-19 United Technologies Corporation Gas turbine engine airfoil
US9140127B2 (en) 2014-02-19 2015-09-22 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
US10570915B2 (en) 2014-02-19 2020-02-25 United Technologies Corporation Gas turbine engine airfoil
EP3108101B1 (en) 2014-02-19 2022-04-20 Raytheon Technologies Corporation Gas turbine engine airfoil
US10495106B2 (en) 2014-02-19 2019-12-03 United Technologies Corporation Gas turbine engine airfoil
EP3108100B1 (en) 2014-02-19 2021-04-14 Raytheon Technologies Corporation Gas turbine engine fan blade
EP2921647A1 (en) 2014-03-20 2015-09-23 Alstom Technology Ltd Gas turbine blade comprising bended leading and trailing edges
WO2015153411A1 (en) * 2014-04-02 2015-10-08 United Technologies Corporation Gas turbine engine airfoil
US10060263B2 (en) * 2014-09-15 2018-08-28 United Technologies Corporation Incidence-tolerant, high-turning fan exit stator
WO2016093811A1 (en) 2014-12-10 2016-06-16 General Electric Company Compressor end-wall treatment having a bent profile
EP3051142B1 (en) 2015-01-28 2017-10-11 MTU Aero Engines GmbH Gas turbine axial compressor
EP3081751B1 (en) * 2015-04-14 2020-10-21 Ansaldo Energia Switzerland AG Cooled airfoil and method for manufacturing said airfoil
FR3040071B1 (en) * 2015-08-11 2020-03-27 Safran Aircraft Engines TURBOMACHINE ROTOR DAWN
GB201519946D0 (en) 2015-11-12 2015-12-30 Rolls Royce Plc Compressor
GB2544735B (en) * 2015-11-23 2018-02-07 Rolls Royce Plc Vanes of a gas turbine engine
US10196898B2 (en) 2015-11-24 2019-02-05 General Electric Company Turbine airfoil with passive morphing structure
US10221859B2 (en) 2016-02-08 2019-03-05 General Electric Company Turbine engine compressor blade
US11248622B2 (en) * 2016-09-02 2022-02-15 Raytheon Technologies Corporation Repeating airfoil tip strong pressure profile
GB201707811D0 (en) * 2017-05-16 2017-06-28 Rolls Royce Plc Compressor aerofoil member
GB2566047B (en) * 2017-08-31 2019-12-11 Rolls Royce Plc Gas turbine engine
GB2566045B (en) 2017-08-31 2019-12-11 Rolls Royce Plc Gas turbine engine
US20190106989A1 (en) * 2017-10-09 2019-04-11 United Technologies Corporation Gas turbine engine airfoil
EP3502482B1 (en) * 2017-12-20 2020-08-26 Ansaldo Energia Switzerland AG Compressor blade with modified stagger angle spanwise distribution
JP6953322B2 (en) * 2018-02-01 2021-10-27 本田技研工業株式会社 How to determine the shape of the fan blade
US11181120B2 (en) * 2018-11-21 2021-11-23 Honeywell International Inc. Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution
GB201917171D0 (en) 2019-11-26 2020-01-08 Rolls Royce Plc Gas turbine engine
CN111156195B (en) * 2020-01-07 2023-11-17 哈尔滨工程大学 Compressor blade leading edge structure
US11286779B2 (en) * 2020-06-03 2022-03-29 Honeywell International Inc. Characteristic distribution for rotor blade of booster rotor
US11371354B2 (en) 2020-06-03 2022-06-28 Honeywell International Inc. Characteristic distribution for rotor blade of booster rotor
US12509988B2 (en) 2024-06-14 2025-12-30 Pratt & Whitney Canada Corp. Turbine engine airfoil

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US5167489A (en) * 1991-04-15 1992-12-01 General Electric Company Forward swept rotor blade
EP1505302A1 (en) * 2003-08-05 2005-02-09 General Electric Company Compressor airfoil
GB2431697A (en) * 2005-08-22 2007-05-02 Gen Electric Fan blade having maximum forward sweep at tip
US20080118362A1 (en) * 2006-11-16 2008-05-22 Siemens Power Generation, Inc. Transonic compressor rotors with non-monotonic meanline angle distributions
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Also Published As

Publication number Publication date
EP2689138A2 (en) 2014-01-29
CA2830257A1 (en) 2012-10-04
US8702398B2 (en) 2014-04-22
JP2014513230A (en) 2014-05-29
CN103814192B (en) 2015-08-19
US20120244005A1 (en) 2012-09-27
WO2012134833A2 (en) 2012-10-04
JP6060145B2 (en) 2017-01-11
CN103814192A (en) 2014-05-21

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