Device and method for testing the integrity of a helicopter turbine engine rapid restart system
US10253699B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 21, 2015 |
| Grant date | Apr 9, 2019 |
| Priority date | — |
| Expiry date | Nov 7, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
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device has an apparatus configured to withdraw pressurized air from the turboshaft engine and a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas.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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.