Title:
AIRCRAFT COMPONENT AND GAS TURBINE ENGINE FOR AIRCRAFT
Document Type and Number:
WIPO Patent Application WO/2017/134844
Kind Code:
A1
Abstract:
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).
More Like This:
| JP2009097094 | NICKEL-BASE SUPERALLOY |
| JP4641916 | Turbine nozzle with cooled corners |
| JP6604939 | Control system, control method and gas turbine engine |
Inventors:
FUJISAWA RYUTARO (JP)
ONISHI TOMOYUKI (JP)
UETSUKI YASUYUKI (JP)
HANADA TADAYUKI (JP)
FUJIMOTO YOHEI (JP)
OTA TAKAFUMI (JP)
ONISHI TOMOYUKI (JP)
UETSUKI YASUYUKI (JP)
HANADA TADAYUKI (JP)
FUJIMOTO YOHEI (JP)
OTA TAKAFUMI (JP)
Application Number:
PCT/JP2016/064604
Publication Date:
August 10, 2017
Filing Date:
May 17, 2016
Export Citation:
Assignee:
MITSUBISHI HEAVY IND AERO ENGINES LTD (JP)
International Classes:
F02C7/00; F01D25/24; F02C7/20; F02K3/06; F23R3/60
Foreign References:
| JP2003232520A | 2003-08-22 | |||
| JPH11257016A | 1999-09-21 | |||
| JPH07208110A | 1995-08-08 | |||
| JPS49130206U | 1974-11-08 | |||
| US8511089B2 | 2013-08-20 |
Other References:
See also references of EP 3399170A4
Attorney, Agent or Firm:
SAKAI INTERNATIONAL PATENT OFFICE (JP)
Download PDF: