Title:
ヘリコプタータービンエンジンの迅速な再起動システムの完全性を試験するための装置および方法
Document Type and Number:
Japanese Patent JP6545260
Kind Code:
B2
Abstract:
A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter, includes a pneumatic turbine that is mechanically connected to the turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurized air from the turboshaft engine and a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas. The device further includes a sensor for determining the rotational speed of the pneumatic turbine.
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Inventors:
Romance
Baze, Jean-Michel
Sergine, Camel
Marconi, Patrick
Jerome, Iligogen
Runfort, Stefan
Baze, Jean-Michel
Sergine, Camel
Marconi, Patrick
Jerome, Iligogen
Runfort, Stefan
Application Number:
JP2017516457A
Publication Date:
July 17, 2019
Filing Date:
September 21, 2015
Export Citation:
Assignee:
Saffron Helicopter Engines
International Classes:
G01M15/14; B64C27/12; B64F5/60; F01D25/00; F02C6/08; F02C7/00; F02C7/262; F02C7/277
Domestic Patent References:
| JP2013544329A | ||||
| JP61096142A | ||||
| JP11093812A |
Foreign References:
| US20140178175 | ||||
| US8291715 |
Attorney, Agent or Firm:
Kawaguchi International Patent Office