Intake liner for a gas turbine engine
US8931252B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 13, 2012 |
| Grant date | Jan 13, 2015 |
| Priority date | — |
| Expiry date | Jan 9, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0645
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine having a rotational axis, an intake and a compressed gas source; the intake includes a lining having a facing which defines an inlet surface and an array of holes; the array of holes includes at least a first set of holes and a second set of holes, the holes of the first set of holes are angled a relative to a radial line and the holes of the second set of holes are angled β relative to the radial line; the angles α and β are different. An active flow control arrangement including a compressed gas supply pipe, a valve arrangement, a controller, a compressed gas distribution pipe may be provided. Compressed gas may be provided to prevent the formation of separation of a main gas flow through the intake and prevent or remove ice accretion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.