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1. (WO2018140130) METHOD AND SYSTEM FOR A GAS TURBINE ENGINE WITH A STAGE TWO BLADE COOLING DELIVERY CIRCUIT
Latest bibliographic data on file with the International Bureau    Submit observation

Pub. No.: WO/2018/140130 International Application No.: PCT/US2017/063315
Publication Date: 02.08.2018 International Filing Date: 27.11.2017
IPC:
F02C 9/18 (2006.01) ,F02C 7/143 (2006.01) ,F01D 25/12 (2006.01) ,F02C 6/04 (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
9
Controlling gas-turbine plants; Controlling fuel supply in air-breathing jet-propulsion plants
16
Control of working fluid flow
18
by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
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
14
of fluids in the plant
141
of working fluid
143
before or between the compressor stages
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
25
Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
08
Cooling; Heating; Heat insulation
12
Cooling
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
6
Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
04
Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
Applicants: GENERAL ELECTRIC COMPANY[US/US]; 1 River Road Schenectady, NY 12345, US
Inventors: JOHNSON, Brian, David; US
WASLO, Daniel; US
Agent: KACHUR, Pamela A.; US
KACHUR, Pamela, A.; US
WINTER, Catherine, J.; US
GNIBUS, Michael, M.; US
MIDGLEY, Stephen, G.; US
Priority Data:
15/401,46109.01.2017US
Title (EN) METHOD AND SYSTEM FOR A GAS TURBINE ENGINE WITH A STAGE TWO BLADE COOLING DELIVERY CIRCUIT
(FR) PROCÉDÉ ET SYSTÈME POUR UN MOTEUR À TURBINE À GAZ AVEC UN CIRCUIT DE DISTRIBUTION DE REFROIDISSEMENT DE PALE À DEUX ÉTAGES
Abstract:
(EN) The turbine includes a first turbine rotor disc, a second turbine rotor disc, a first source of cooling fluid, and a first cooling fluid conduit. The first turbine rotor disc has a first outer circumference and a first plurality of blades spaced along the first outer circumference. The second turbine rotor disc has a second outer circumference and a second plurality of blades spaced along the second outer circumference. The first cooling fluid conduit is configured to channel a first flow of cooling fluid from the first source of cooling fluid through the first turbine rotor disc to a blade of the second plurality of blades.
(FR) La turbine comprend un premier disque de rotor de turbine, un second disque de rotor de turbine, une première source de fluide de refroidissement, et un premier conduit de fluide de refroidissement. Le premier disque de rotor de turbine comprend une première circonférence extérieure et une première pluralité de pales espacées le long d'une première circonférence extérieure. Le second disque de rotor de turbine possède une seconde circonférence extérieure et une seconde pluralité de pales espacées le long d'une seconde circonférence extérieure. Le premier conduit de fluide de refroidissement est conçu pour canaliser un premier écoulement de fluide de refroidissement d'une première source de fluide de refroidissement à travers un disque de rotor de turbine vers une pale de la seconde pluralité de pales.
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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, JP, 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: English (EN)
Filing Language: English (EN)