Title:
AIRCRAFT ENGINE
Document Type and Number:
WIPO Patent Application WO/2012/137844
Kind Code:
A1
Abstract:
Provided is a compact aircraft engine obtained by configuring the aircraft engine so that an accessory can be directly supported without the use of an accessory gear box.
An aircraft engine (E) is provided with: a take-off shaft (11) which has a base end connected to the rotating shaft of the engine, extends to the outside of the engine (E) in the radial direction, and has an accessory (1) connected to the front end of the take-off shaft (11); and a mounting pad (12) provided to the engine body (FC) and having the accessory (1) mounted thereto. The mounting pad (12) forms the outer periphery of an opening (48) through which the take-off shaft (11) penetrates. The opening (48) is closed by a cover (47) through which the take-off shaft (11) penetrates and by a seal member (49) for sealing between the cover (47) and the take-off shaft (11).
More Like This:
| WO/2014/014750 | JOINT BETWEEN AIRFOIL AND SHROUD |
| JP2790865 | [Title of Invention] Turbo Engine |
| WO/2014/036554 | ASSEMBLY FOR MOUNTING A TURBINE ENGINE TO A PYLON |
Inventors:
GOI TATSUHIKO (JP)
TANAKA KENICHIRO (JP)
WATANABE KOJI (JP)
FUJII ISAO (JP)
TANAKA KENICHIRO (JP)
WATANABE KOJI (JP)
FUJII ISAO (JP)
Application Number:
PCT/JP2012/059247
Publication Date:
October 11, 2012
Filing Date:
April 04, 2012
Export Citation:
Assignee:
KAWASAKI HEAVY IND LTD (JP)
GOI TATSUHIKO (JP)
TANAKA KENICHIRO (JP)
WATANABE KOJI (JP)
FUJII ISAO (JP)
GOI TATSUHIKO (JP)
TANAKA KENICHIRO (JP)
WATANABE KOJI (JP)
FUJII ISAO (JP)
International Classes:
F02C7/32; B64D41/00; F01D15/10; F02C7/00; F02C7/36
Foreign References:
| EP1980732A2 | 2008-10-15 | |||
| JP2009532613A | 2009-09-10 | |||
| JP2008190526A | 2008-08-21 | |||
| US7386983B2 | 2008-06-17 | |||
| US7707909B2 | 2010-05-04 |
Other References:
See also references of EP 2696057A4
Attorney, Agent or Firm:
SUGIMOTO, SHUJI (JP)
Shuji Sugimoto (JP)
Shuji Sugimoto (JP)
Download PDF:
Claims: