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1. WO2012133630 - COMBUSTOR FOR GAS TURBINE ENGINE AND GAS TURBINE

Publication Number WO/2012/133630
Publication Date 04.10.2012
International Application No. PCT/JP2012/058330
International Filing Date 29.03.2012
IPC
F23R 3/06 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3Continuous combustion chambers using liquid or gaseous fuel
02characterised by the air-flow or gas-flow configuration
04Air inlet arrangements
06Arrangement of apertures along the flame tube
F02C 7/18 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
12Cooling of plants
16characterised by cooling medium
18the medium being gaseous, e.g. air
CPC
F02C 7/18
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
12Cooling of plants
16characterised by cooling medium
18the medium being gaseous, e.g. air
F23R 2900/03041
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
2900Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
03041Effusion cooled combustion chamber walls or domes
F23R 2900/03044
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
2900Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
03044Impingement cooled combustion chamber walls or subassemblies
F23R 2900/03045
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
2900Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
03045Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
F23R 3/002
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3Continuous combustion chambers using liquid or gaseous fuel
002Wall structures
F23R 3/06
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3Continuous combustion chambers using liquid or gaseous fuel
02characterised by the air-flow or gas-flow configuration
04Air inlet arrangements
06Arrangement of apertures along the flame tube
Applicants
  • 株式会社IHI IHI Corporation [JP]/[JP] (AllExceptUS)
  • 仲俣 千由紀 NAKAMATA, Chiyuki [JP]/[JP] (UsOnly)
  • 大北 洋治 OKITA, Yoji [JP]/[JP] (UsOnly)
  • 細井 潤 HOSOI, Jun [JP]/[JP] (UsOnly)
  • 廣光 永兆 HIROMITSU, Nagayoshi [JP]/[JP] (UsOnly)
  • 平田 淳 HIRATA, Atsushi [JP]/[JP] (UsOnly)
  • 出田 武臣 IDETA, Takeomi [JP]/[JP] (UsOnly)
Inventors
  • 仲俣 千由紀 NAKAMATA, Chiyuki
  • 大北 洋治 OKITA, Yoji
  • 細井 潤 HOSOI, Jun
  • 廣光 永兆 HIROMITSU, Nagayoshi
  • 平田 淳 HIRATA, Atsushi
  • 出田 武臣 IDETA, Takeomi
Agents
  • 三好 秀和 MIYOSHI, Hidekazu
Priority Data
2011-07848631.03.2011JP
Publication Language Japanese (JA)
Filing Language Japanese (JA)
Designated States
Title
(EN) COMBUSTOR FOR GAS TURBINE ENGINE AND GAS TURBINE
(FR) CHAMBRE DE COMBUSTION POUR UN MOTEUR DE TURBINE À GAZ ET TURBINE À GAZ
(JA) ガスタービンエンジン用燃焼器及びガスタービン
Abstract
(EN)
A combustor for gas turbine engine, wherein: a plurality of impingement-cooling holes (39) is formed passing through an external wall (35) of a liner for cooling air (CA) to blow out towards the outer surface of an interior wall (37) of the liner; a plurality of heat transfer pins (43) is formed passing through the outer surface of the interior wall (37) of the liner; a plurality of effusion cooling holes (41) is formed passing through the interior wall (37) of the liner for cooling air (CA) to blow out along the inner surface of the interior wall (37) of the liner. The apical surface of each heat transfer pin (43) is not in contact with the inner surface of the external wall (35) of the liner and the ratio (H/D) of the height (H) of the heat transfer pin (43) to the equivalent diameter (D) of the impingement-cooling hole (39) is set to be 1.0 - 3.0.
(FR)
La présente invention se rapporte à une chambre de combustion pour un moteur de turbine à gaz, une pluralité de trous de refroidissement par choc (39) étant formés de façon à traverser une paroi externe (35) d'une chemise afin que l'air de refroidissement (CA) souffle vers la surface externe d'une paroi intérieure (37) de la chemise; une pluralité de broches de transfert de chaleur (43) étant formées de façon à traverser la surface externe de la paroi intérieure (37) de la chemise; une pluralité de trous de refroidissement par effusion (41) étant formés de façon à traverser la paroi intérieure (37) de la chemise afin que l'air de refroidissement (CA) souffle le long de la surface interne de la paroi intérieure (37) de la chemise. La surface apicale de chaque broche de transfert de chaleur (43) n'est pas en contact avec la surface interne de la paroi externe (35) de la chemise et le rapport (H/D) entre la hauteur (H) de la broche de transfert de chaleur (43) et le diamètre équivalent (D) du trou de refroidissement par choc (39) est réglé pour varier entre 1,0 et 3,0.
(JA)
 ガスタービンエンジン用燃焼器において、ライナ外壁(35)に冷却空気(CA)をライナ内壁(37)の外表面に向かって噴き出すための複数のインピンジ冷却孔(39)が貫通して形成され、ライナ内壁(37)の外表面に複数の伝熱ピン(43)が形成され、ライナ内壁(37)に冷却空気(CA)をライナ内壁(37)の内表面に沿って噴き出すための複数のエフュージョン冷却孔(41)が貫通して形成され、各伝熱ピン(43)の先端面がライナ外壁(35)の内表面に対して非接触であって、伝熱ピン(43)の高さ寸法(H)のインピンジ冷却孔(39)の等価直径(D)に対する比(H/D)が1.0~3.0に設定されている。
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