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1. WO2015126452 - GAS TURBINE ENGINE AIRFOIL

Publication Number WO/2015/126452
Publication Date 27.08.2015
International Application No. PCT/US2014/052434
International Filing Date 25.08.2014
IPC
F01D 5/14 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members
12Blades
14Form or construction
F02C 7/00 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7Features, component parts, details or accessories, not provided for in, or of interest apart from, groups F02C1/-F02C6/158; Air intakes for jet-propulsion plants
F04D 29/38 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
04POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
DNON-POSITIVE-DISPLACEMENT PUMPS
29Details, component parts, or accessories
26Rotors specially adapted for elastic fluids
32for axial-flow pumps
38Blades
CPC
F01D 5/141
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members
12Blades
14Form or construction
141Shape, i.e. outer, aerodynamic form
F02C 3/04
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
3Gas-turbine plants characterised by the use of combustion products as the working fluid
04having a turbine driving a compressor
F02C 7/36
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7Features, 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
36Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
F02K 3/06
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
3Plants including a gas turbine driving a compressor or a ducted fan
02in which part of the working fluid by-passes the turbine and combustion chamber
04the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
06with front fan
F04D 29/324
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
DNON-POSITIVE-DISPLACEMENT PUMPS
29Details, component parts, or accessories
26Rotors specially for elastic fluids
32for axial flow pumps
321for axial flow compressors
324Blades
F04D 29/325
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
DNON-POSITIVE-DISPLACEMENT PUMPS
29Details, component parts, or accessories
26Rotors specially for elastic fluids
32for axial flow pumps
325for axial flow fans
Applicants
  • UNITED TECHNOLOGIES CORPORATION [US]/[US]
Inventors
  • GALLAGHER, Edward, J.
  • MONZON, Byron, R.
  • LIU, Ling
  • LI, Linda, S.
  • WHITLOW, Darryl
  • FORD, Barry, M.
Agents
  • GOTTSCHALK, William, S.
Priority Data
61/941,75219.02.2014US
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) GAS TURBINE ENGINE AIRFOIL
(FR) SURFACE PORTANTE DE MOTEUR À TURBINE À GAZ
Abstract
(EN)
In one exemplary embodiment, an airfoil for a turbine engine includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to tangential leading and trailing edge curves and a tangential stacking offset curve. The airfoil extends from a root. A zero tangential reference point corresponds to tangential center of the root. YLE corresponds to a tangential distance from a leading edge to the reference point at a given span position. YTE corresponds to a tangential distance from a trailing edge to the reference point at a given span position. Yd corresponds to a tangential stacking offset at a given span position. (YLE-Yd)/(Yd-YTE) at 40% span position is about 1.5 and (YLE-Yd)/(Yd-YTE) at 20% span position is about 2.
(FR)
Selon un mode de réalisation illustratif, la présente invention concerne une surface portante pour un moteur à turbine comprenant un côté pression et un côté aspiration s'étendant dans une direction radiale depuis une position 0 % d'extension au niveau d'un emplacement de trajet d'écoulement intérieure jusqu'à une position 100 % d'extension au niveau d'une pointe de surface portante. La géométrie de la surface portante correspond à des courbes de bord d'attaque et de bord de fuite tangentielles et à une courbe de décalage d'empilement tangentielle. La surface portante s'étend depuis une emplanture. Un point de référence tangentiel nul correspond au centre tangentiel de l'emplanture. YLEcorrespond à une distance tangentielle depuis un bord d'attaque jusqu'au point de référence dans une position d'extension donnée. YTE correspond à une distance tangentielle depuis un bord de fuite jusqu'au point de référence dans une position d'extension donnée. Yd correspond à un décalage d'empilement tangentiel dans une position d'extension donnée. (YLE-Yd)/(Yd-YTE) dans une position 40% d'extension est d'environ 1,5 et YLE-Yd)/(Yd-YTE) dans une position 20% d'extension est d'environ 2.
Also published as
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