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1. (WO2018101190) HIGH-TEMPERATURE COMPONENT FOR GAS TURBINE, GAS TURBINE BLADE, AND GAS TURBINE
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Pub. No.: WO/2018/101190 International Application No.: PCT/JP2017/042332
Publication Date: 07.06.2018 International Filing Date: 27.11.2017
IPC:
F02C 7/18 (2006.01) ,F01D 5/18 (2006.01) ,F01D 9/02 (2006.01) ,F01D 9/04 (2006.01) ,F01D 11/08 (2006.01)
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02
COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
C
GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7
Features, component parts, details or accessories, not provided for in, or of interest apart from, groups F02C1/-F02C6/158; Air intakes for jet-propulsion plants
12
Cooling of plants
16
characterised by cooling medium
18
the medium being gaseous, e.g. air
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01
MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
D
NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5
Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members
12
Blades
14
Form or construction
18
Hollow blades; Heating, heat-insulating, or cooling means on blades
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01
MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
D
NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
9
Stators
02
Nozzles; Nozzle boxes; Stator blades; Guide conduits
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01
MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
D
NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
9
Stators
02
Nozzles; Nozzle boxes; Stator blades; Guide conduits
04
forming ring or sector
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01
MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
D
NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
11
Preventing or minimising internal leakage of working fluid, e.g. between stages
08
for sealing space between rotor blade tips and stator
Applicants:
三菱重工業株式会社 MITSUBISHI HEAVY INDUSTRIES, LTD. [JP/JP]; 東京都港区港南二丁目16番5号 16-5, Konan 2-Chome, Minato-ku, Tokyo 1088215, JP
Inventors:
石黒 達男 ISHIGURO, Tatsuo; JP
Agent:
誠真IP特許業務法人 SEISHIN IP PATENT FIRM, P.C.; 東京都港区三田三丁目13番16号 三田43MTビル13階 Mita 43MT Building 13th Floor, 13-16, Mita 3-Chome, Minato-ku, Tokyo 1080073, JP
Priority Data:
2016-23204430.11.2016JP
Title (EN) HIGH-TEMPERATURE COMPONENT FOR GAS TURBINE, GAS TURBINE BLADE, AND GAS TURBINE
(FR) COMPOSANT À HAUTE-TEMPÉRATURE POUR TURBINE À GAZ, AUBE DE TURBINE À GAZ ET TURBINE À GAZ
(JA) ガスタービン用高温部品、ガスタービンの翼及びガスタービン
Abstract:
(EN) A high-temperature component (10) for a gas turbine is provided with a main body part (40) and a porous part (42) through which a cooling gas can pass, and is configured such that, in accordance with one or both distributions of a heat load and a pressure difference acting on the main body part (40) or the porous part (42), a distribution is created in the arrangement of the porous part (42) or in the through-flow rate of the cooling gas in the porous part (42). A gas turbine blade, which constitutes at least a trailing edge part of a blade part, is also provided with a porous part (42) through which the cooling gas can pass, the porous part (42) having a porosity distribution such that the cooling gas flows out from the interior of the blade part to a trailing edge of the blade part through the porous part (42).
(FR) Composant à haute-température (10) pour une turbine à gaz pourvu d'une partie corps principal (40) et d'une partie poreuse (42) à travers lequel un gaz de refroidissement peut passer, et conçu de telle sorte que, conformément à une ou aux deux distributions d'une charge de chaleur et d'une différence de pression agissant sur la partie corps principal (40) ou la partie poreuse (42), une distribution est créée dans l'agencement de la partie poreuse (42) ou dans le débit de passage du gaz de refroidissement dans la partie poreuse (42). Une aube de turbine à gaz, qui constitue au moins une partie de bord de fuite d'une partie d'aube, est également pourvue d'une partie poreuse (42) à travers laquelle le gaz de refroidissement peut passer, la partie poreuse (42) ayant une distribution de porosité de telle sorte que le gaz de refroidissement s'écoule depuis l'intérieur de la partie d'aube jusqu'à un bord de fuite de la partie d'aube à travers la partie poreuse (42).
(JA) ガスタービン用高温部品(10)は、本体部(40)と、冷却ガスが通過可能な多孔質部(42)と、を備え、本体部(40)又は多孔質部(42)に作用する熱負荷及び圧力差の分布のうち一方又は両方に応じて、多孔質部(42)の配置又は多孔質部(42)における冷却ガスの通過流量に分布をもたせるように構成されている。また、ガスタービンの翼は、翼部の少なくとも後縁部を構成し、冷却ガスが通過可能な多孔質部(42)を備え、多孔質部(42)は、翼部の内部から多孔質部(42)を通じて翼部の後縁から冷却ガスが流出するように、気孔率の分布を有する。
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Designated States: AE, AG, AL, AM, AO, AT, AU, AZ, BA, BB, BG, BH, BN, BR, BW, BY, BZ, CA, CH, CL, CN, CO, CR, CU, CZ, DE, DJ, DK, DM, DO, DZ, EC, EE, EG, ES, FI, GB, GD, GE, GH, GM, GT, HN, HR, HU, ID, IL, IN, IR, IS, JO, KE, KG, KH, KN, KP, KR, KW, KZ, LA, LC, LK, LR, LS, LU, LY, MA, MD, ME, MG, MK, MN, MW, MX, MY, MZ, NA, NG, NI, NO, NZ, OM, PA, PE, PG, PH, PL, PT, QA, RO, RS, RU, RW, SA, SC, SD, SE, SG, SK, SL, SM, ST, SV, SY, TH, TJ, TM, TN, TR, TT, TZ, UA, UG, US, UZ, VC, VN, ZA, ZM, ZW
African Regional Intellectual Property Organization (ARIPO) (BW, GH, GM, KE, LR, LS, MW, MZ, NA, RW, SD, SL, ST, SZ, TZ, UG, ZM, ZW)
Eurasian Patent Office (AM, AZ, BY, KG, KZ, RU, TJ, TM)
European Patent Office (EPO) (AL, AT, BE, BG, CH, CY, CZ, DE, DK, EE, ES, FI, FR, GB, GR, HR, HU, IE, IS, IT, LT, LU, LV, MC, MK, MT, NL, NO, PL, PT, RO, RS, SE, SI, SK, SM, TR)
African Intellectual Property Organization (BF, BJ, CF, CG, CI, CM, GA, GN, GQ, GW, KM, ML, MR, NE, SN, TD, TG)
Publication Language: Japanese (JA)
Filing Language: Japanese (JA)