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1. WO2020115410 - TURBINE OR COMPRESSOR FOR GAS TURBINE ENGINE WITH LIMITED LOSS OF CLEARANCE

Publication Number WO/2020/115410
Publication Date 11.06.2020
International Application No. PCT/FR2019/052878
International Filing Date 02.12.2019
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
F01D 5/20 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
20Specially-shaped blade tips to seal space between tips and stator
CPC
F01D 5/143
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
142of the blades of successive rotor or stator blade-rows
143Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
F01D 5/145
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
145Means for influencing boundary layers or secondary circulations
F01D 5/20
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
20Specially-shaped blade tips to seal space between tips and stator
F05D 2240/307
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2240Components
20Rotors
30Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
307related to the tip of a rotor blade
F05D 2250/71
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2250Geometry
70Shape
71curved
Applicants
  • SAFRAN [FR]/[FR]
Inventors
  • TANG, Etienne, Yung
Agents
  • DESORMIERE, Pierre-Louis
  • DAVID, Alain
  • HEALY, Erwan
  • LAIK, Eric
Priority Data
187238205.12.2018FR
Publication Language French (FR)
Filing Language French (FR)
Designated States
Title
(EN) TURBINE OR COMPRESSOR FOR GAS TURBINE ENGINE WITH LIMITED LOSS OF CLEARANCE
(FR) TURBINE OU DE COMPRESSEUR POUR MOTEUR A TURBINE A GAZ A PERTES DE JEU LIMITEES
Abstract
(EN)
The invention relates to a turbine or a compressor for a gas turbine engine, comprising a plurality of blades (16) surrounded by an external ring (8) defining an external flow line (8a) for a gas stream to flow, each blade, on one hand, extending axially between a leading edge (20) and a trailing edge (22) and, on the other hand, extending radially between a foot (24) and a head (26), a radial clearance remaining between the external ring and the head of the mobile blades, the external ring progressively increasing in diameter between the leading edge and the trailing edge of the blades and finishing with an upwards step (28) downstream from the trailing edge of the blades, the head of the blades being raised near the trailing edge in order to conserve a predetermined radial clearance.
(FR)
L'invention concerne une turbine ou un compresseur pour moteur à turbine à gaz, comprenant une pluralité d'aubes (16) entourées par un anneau externe (8) délimitant une ligne de veine externe (8a) d'écoulement d'un flux gazeux, chaque aube s'étendant, d'une part axialement entre un bord d'attaque (20) et un bord de fuite (22) et, d'autre part radialement entre un pied (24) et une tête (26), un jeu radial subsistant entre l'anneau externe et la tête des aubes mobiles, l'anneau externe présentant une augmentation progressive de son diamètre entre le bord d'attaque et le bord de fuite des aubes et finissant par une marche montante (28) en aval du bord de fuite des aubes, la tête des aubes présentant un rehaussement au voisinage du bord de fuite afin de conserver un jeu radial prédéterminé.
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