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1. (WO2017134844) AIRCRAFT COMPONENT AND GAS TURBINE ENGINE FOR AIRCRAFT
Latest bibliographic data on file with the International Bureau

Pub. No.: WO/2017/134844 International Application No.: PCT/JP2016/064604
Publication Date: 10.08.2017 International Filing Date: 17.05.2016
IPC:
F02C 7/00 (2006.01) ,F01D 25/24 (2006.01) ,F02C 7/20 (2006.01) ,F02K 3/06 (2006.01) ,F23R 3/60 (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
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
24
Casings; Casing parts, e.g. diaphragms, casing fastenings
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
20
Mounting or supporting of plant; Accommodating heat expansion or creep
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02
COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
K
JET-PROPULSION PLANTS
3
Plants including a gas turbine driving a compressor or a ducted fan
02
in which part of the working fluid by-passes the turbine and combustion chamber
04
the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type
06
with front fan
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
60
Support structures; Attaching or mounting means
Applicants:
三菱重工航空エンジン株式会社 MITSUBISHI HEAVY INDUSTRIES AERO ENGINES, LTD. [JP/JP]; 愛知県小牧市東田中1200番地 1200, Higashi-tanaka, Komaki-shi, Aichi 4850826, JP
Inventors:
藤澤 竜太朗 FUJISAWA, Ryutaro; JP
大西 智之 ONISHI, Tomoyuki; JP
植月 康之 UETSUKI, Yasuyuki; JP
花田 忠之 HANADA, Tadayuki; JP
藤本 洋平 FUJIMOTO, Yohei; JP
大田 貴史 OTA, Takafumi; JP
Agent:
特許業務法人酒井国際特許事務所 SAKAI INTERNATIONAL PATENT OFFICE; 東京都千代田区霞が関3丁目8番1号 虎の門三井ビルディング Toranomon Mitsui Building, 8-1, Kasumigaseki 3-chome, Chiyoda-ku, Tokyo 1000013, JP
Priority Data:
2016-01999604.02.2016JP
Title (EN) AIRCRAFT COMPONENT AND GAS TURBINE ENGINE FOR AIRCRAFT
(FR) ÉLÉMENT D'AÉRONEF ET MOTEUR À TURBINE À GAZ POUR AÉRONEF
(JA) 航空部品及び航空用ガスタービンエンジン
Abstract:
(EN) Provided is an aircraft component used in a gas turbine engine for an aircraft, the aircraft component comprising an annular part having an outer peripheral surface, and a boss part (7) that radially protrudes from the outer peripheral surface of the annular part. In the boss part (7), an opening (10) and bolt holes (11) are formed penetrating in the radial direction with predetermined intervals therebetween. A recessed part (15) at which a portion of the boss part (7) is missing is formed in the boss part (7) on the periphery of the opening (10) and the bolt holes (11). The recessed part (15) is formed from the peripheral edge of the boss part (7) toward a space between the opening (10) and the bolt holes (11).
(FR) L'invention concerne un élément d'aéronef utilisé dans un moteur à turbine à gaz pour un aéronef, lequel élément d'aéronef comprend une partie annulaire ayant une surface périphérique externe, et une partie de protubérance (7) qui fait saillie radialement à partir de la surface périphérique externe de la partie annulaire. Dans la partie de protubérance (7), une ouverture (10) et des trous de boulon (11) sont formés, pénétrant dans la direction radiale avec des intervalles prédéterminés entre eux. Une partie en creux (15), dans laquelle une partie de la partie de protubérance (7) est manquante, est formée dans la partie de protubérance (7) sur la périphérie de l'ouverture (10) et des trous de boulon (11). La partie en creux (15) est formée à partir du bord périphérique de la partie de protubérance (7) vers un espace entre l'ouverture (10) et les trous de boulon (11).
(JA) 航空用ガスタービンエンジンに用いられる航空部品において、外周面を有する円環部と、円環部の外周面から径方向に突出するボス部(7)と、を有し、ボス部(7)には、所定の間隔を空けて、開口部(10)とボルト孔(11)とが径方向に貫通形成され、開口部(10)とボルト孔(11)との周囲のボス部(7)には、ボス部(7)の一部が欠損するぬすみ部(15)が形成されている。ぬすみ部(15)は、ボス部(7)の周縁から、開口部(10)とボルト孔(11)との間に向かって形成されている。
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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, DK, DM, DO, DZ, EC, EE, EG, ES, FI, GB, GD, GE, GH, GM, GT, HN, HR, HU, ID, IL, IN, IR, IS, KE, KG, KN, KP, KR, 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 Organization (AM, AZ, BY, KG, KZ, RU, TJ, TM)
European Patent Office (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)
Also published as:
CA3013172EP3399170US20190032517