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1. (WO1991008421) COMBUSTION APPARATUS AND METHOD FOR A TURBINE ENGINE
Latest bibliographic data on file with the International Bureau

Pub. No.: WO/1991/008421 International Application No.: PCT/US1990/006689
Publication Date: 13.06.1991 International Filing Date: 15.11.1990
Chapter 2 Demand Filed: 27.05.1991
IPC:
F23R 3/06 (2006.01) ,F23R 3/12 (2006.01) ,F23R 3/28 (2006.01) ,F23R 3/50 (2006.01) ,F23R 3/54 (2006.01)
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23
COMBUSTION APPARATUS; COMBUSTION PROCESSES
R
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3
Continuous combustion chambers using liquid or gaseous fuel
02
characterised by the air-flow or gas-flow configuration
04
Air inlet arrangements
06
Arrangement of apertures along the flame tube
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23
COMBUSTION APPARATUS; COMBUSTION PROCESSES
R
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3
Continuous combustion chambers using liquid or gaseous fuel
02
characterised by the air-flow or gas-flow configuration
04
Air inlet arrangements
10
for primary air
12
inducing a vortex
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23
COMBUSTION APPARATUS; COMBUSTION PROCESSES
R
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3
Continuous combustion chambers using liquid or gaseous fuel
28
characterised by the fuel supply
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23
COMBUSTION APPARATUS; COMBUSTION PROCESSES
R
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3
Continuous combustion chambers using liquid or gaseous fuel
42
characterised by the arrangement or form of the flame tubes or combustion chambers
50
Combustion chambers comprising an annular flame tube within an annular casing
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23
COMBUSTION APPARATUS; COMBUSTION PROCESSES
R
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3
Continuous combustion chambers using liquid or gaseous fuel
42
characterised by the arrangement or form of the flame tubes or combustion chambers
54
Reverse-flow combustion chambers
Applicants:
ALLIED-SIGNAL INC. [US/US]; Law Department (C.A. McNally) P.O. Box 2245R Morristown, NJ 07962-2245, US
Inventors:
HAASIS, John, M.; US
Agent:
MASSUNG, Howard, G.; Allied-Signal Inc. Law Dept. (C.A. McNally) 101 Columbia Road P.O. Box 2245 Morristown, NJ 07962-2245, US
McFARLAND, James, W.; Allied-Signal Inc. Law Department (C.A. McNally) P.O. Box 2245 Morristown, NJ 07962, US
Priority Data:
446,23305.12.1989US
Title (EN) COMBUSTION APPARATUS AND METHOD FOR A TURBINE ENGINE
(FR) PROCEDE ET APPAREIL DE COMBUSTION POUR UN MOTEUR A TURBINE
Abstract:
(EN) A combustion structure (34) for a turbine engine (10) includes an annular combustion cavity (52) into which flows a part of each of a plurality of radially outwardly flowing primary air jets (72) to define a rotating toroid (78) of primary combustion air. Plural annular louvers (54, 56, 58, 60) defined in the walls of the combustion cavity provide plural film-like wall cooling air flows moving in agreement with the rotating toroid of primary combustion air. An annular array of circumferentially spaced apart and disposed louvers (88) in a radially outer wall (44) of the combustor structure (34) provide film-like air flows (90) to energize the rotating toroid (78) of combustion air to swirl about the combustion cavity (52).
(FR) Une structure de combustion (34) pour un moteur à turbine (10) comporte une cavité de combustion (52) vers laquelle s'écoule une partie de chacun d'une pluralité de jets d'air primaires (72) à écoulement radial vers l'extérieur, afin de définir un tore rotatif (78) d'air de combustion primaire. Une pluralité de volets d'aération annulaires (54, 56, 58, 60) ménagés dans les parois de la cavité de combustion fournissent une pluralité de flux d'air laminaires refroidissant les parois, lesquels flux d'air s'écoulent en coopération avec le tore rotatif d'air de combustion primaire. Une rangée annulaire de volets d'aération périphériques et espacés (88) ménagés dans une paroi radiale extérieure (44) de la structure de combustion (34) fournissent des flux d'air (90) laminaires afin de provoquer la rotation du tore (78) d'air de combustion dans la cavité de combustion (52)
Designated States: CA, JP
European Patent Office (AT, BE, CH, DE, DK, ES, FR, GB, GR, IT, LU, NL, SE)
Publication Language: English (EN)
Filing Language: English (EN)