SG11201403700YA - Fan stagger angle for geared gas turbine engine - Google Patents

Fan stagger angle for geared gas turbine engine

Info

Publication number
SG11201403700YA
SG11201403700YA SG11201403700YA SG11201403700YA SG11201403700YA SG 11201403700Y A SG11201403700Y A SG 11201403700YA SG 11201403700Y A SG11201403700Y A SG 11201403700YA SG 11201403700Y A SG11201403700Y A SG 11201403700YA SG 11201403700Y A SG11201403700Y A SG 11201403700YA
Authority
SG
Singapore
Prior art keywords
gas turbine
turbine engine
stagger angle
geared gas
fan
Prior art date
Application number
SG11201403700YA
Inventor
Edward J Gallagher
Byron R Monzon
Ling Liu
Linda S Li
Darryl Whitlow
Original Assignee
United Technologies Corp
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=49223147&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=SG11201403700Y(A) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of SG11201403700YA publication Critical patent/SG11201403700YA/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Retarders (AREA)
SG11201403700YA 2012-01-31 2012-12-28 Fan stagger angle for geared gas turbine engine SG11201403700YA (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201261592814P 2012-01-31 2012-01-31
PCT/US2012/072069 WO2013141935A1 (en) 2012-01-31 2012-12-28 Fan stagger angle for geared gas turbine engine

Publications (1)

Publication Number Publication Date
SG11201403700YA true SG11201403700YA (en) 2014-10-30

Family

ID=49223147

Family Applications (1)

Application Number Title Priority Date Filing Date
SG11201403700YA SG11201403700YA (en) 2012-01-31 2012-12-28 Fan stagger angle for geared gas turbine engine

Country Status (4)

Country Link
US (1) US20130340406A1 (en)
EP (3) EP3763916A1 (en)
SG (1) SG11201403700YA (en)
WO (1) WO2013141935A1 (en)

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US8997494B2 (en) * 2012-09-28 2015-04-07 United Technologies Corporation Gas turbine engine fan blade airfoil profile
WO2014163673A2 (en) 2013-03-11 2014-10-09 Bronwyn Power Gas turbine engine flow path geometry
EP3108109B1 (en) 2014-02-19 2023-09-13 Raytheon Technologies Corporation Gas turbine engine fan blade
US10605259B2 (en) 2014-02-19 2020-03-31 United Technologies Corporation Gas turbine engine airfoil
EP3108116B1 (en) * 2014-02-19 2024-01-17 RTX Corporation Gas turbine engine
EP3108106B1 (en) 2014-02-19 2022-05-04 Raytheon Technologies Corporation Gas turbine engine airfoil
EP3108104B1 (en) 2014-02-19 2019-06-12 United Technologies Corporation Gas turbine engine airfoil
US10422226B2 (en) 2014-02-19 2019-09-24 United Technologies Corporation Gas turbine engine airfoil
WO2015178974A2 (en) * 2014-02-19 2015-11-26 United Technologies Corporation Gas turbine engine airfoil
WO2015126452A1 (en) 2014-02-19 2015-08-27 United Technologies Corporation Gas turbine engine airfoil
WO2015175058A2 (en) 2014-02-19 2015-11-19 United Technologies Corporation Gas turbine engine airfoil
WO2015175056A2 (en) 2014-02-19 2015-11-19 United Technologies Corporation Gas turbine engine airfoil
EP3108119B1 (en) 2014-02-19 2023-10-04 RTX Corporation Turbofan engine with geared architecture and lpc blade airfoils
WO2015126451A1 (en) 2014-02-19 2015-08-27 United Technologies Corporation Gas turbine engine airfoil
EP3114321B1 (en) 2014-02-19 2019-04-17 United Technologies Corporation Gas turbine engine airfoil
US10570915B2 (en) 2014-02-19 2020-02-25 United Technologies Corporation Gas turbine engine airfoil
EP3108107B1 (en) * 2014-02-19 2023-10-11 Raytheon Technologies Corporation Turbofan engine with geared architecture and lpc airfoils
WO2015127032A1 (en) 2014-02-19 2015-08-27 United Technologies Corporation Gas turbine engine airfoil
EP3108100B1 (en) 2014-02-19 2021-04-14 Raytheon Technologies Corporation Gas turbine engine fan blade
EP3108118B1 (en) * 2014-02-19 2019-09-18 United Technologies Corporation Gas turbine engine airfoil
US9567858B2 (en) 2014-02-19 2017-02-14 United Technologies Corporation Gas turbine engine airfoil
WO2015175052A2 (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
WO2015175051A2 (en) 2014-02-19 2015-11-19 United Technologies Corporation Gas turbine engine airfoil
US9869190B2 (en) 2014-05-30 2018-01-16 General Electric Company Variable-pitch rotor with remote counterweights
US10072510B2 (en) 2014-11-21 2018-09-11 General Electric Company Variable pitch fan for gas turbine engine and method of assembling the same
US9470093B2 (en) * 2015-03-18 2016-10-18 United Technologies Corporation Turbofan arrangement with blade channel variations
US10669946B2 (en) * 2015-06-05 2020-06-02 Raytheon Technologies Corporation Geared architecture for a gas turbine engine
US10100653B2 (en) 2015-10-08 2018-10-16 General Electric Company Variable pitch fan blade retention system
US10458426B2 (en) 2016-09-15 2019-10-29 General Electric Company Aircraft fan with low part-span solidity
EP3502482B1 (en) * 2017-12-20 2020-08-26 Ansaldo Energia Switzerland AG Compressor blade with modified stagger angle spanwise distribution
US10436035B1 (en) * 2018-07-03 2019-10-08 Rolls-Royce Plc Fan design
GB201810885D0 (en) 2018-07-03 2018-08-15 Rolls Royce Plc High efficiency gas turbine engine
US11236619B2 (en) * 2019-05-07 2022-02-01 Raytheon Technologies Corporation Multi-cover gas turbine engine component
US12065942B2 (en) 2019-11-27 2024-08-20 Rolls-Royce Plc Gas turbine engine fan
US11674435B2 (en) 2021-06-29 2023-06-13 General Electric Company Levered counterweight feathering system
US11795964B2 (en) 2021-07-16 2023-10-24 General Electric Company Levered counterweight feathering system

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US8708660B2 (en) * 2010-05-21 2014-04-29 Alstom Technology Ltd Airfoil for a compressor blade

Also Published As

Publication number Publication date
WO2013141935A1 (en) 2013-09-26
EP2809579A1 (en) 2014-12-10
EP3098384A1 (en) 2016-11-30
EP3098384B1 (en) 2020-05-06
EP2809579A4 (en) 2015-09-30
EP3763916A1 (en) 2021-01-13
US20130340406A1 (en) 2013-12-26
EP2809579B1 (en) 2018-08-22

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