Gas turbine engine variable bleed pivotal flow splitter
AssigneeGeneral Electric Company
InventorsHsin-Tuan Liu, William R. Hines
Life of this patent
Estimating the term…
Abstract
The present invention provides a gas turbine engine with a circumferentially disposed plurality of pivotal flow splitters between compressor sections to bleed off flow and remove particles, particularly ice in the case of an aircraft fan-jet gas turbine engine, by pivoting the leading edge of the splitter into the compressor flow thereby using the total pressure Q of the flow to drive bleed flows overboard and remove particles. In the preferred embodiment the pivotal flow splitter is integral with a booster variable bleed valve (VBV) door, and includes a booster bleed duct means having a bellmouth shaped inducer type inlet to enhance the capture of compressor flow and particle removal
Claims12
A gas turbine engine driven apparatus comprising:
- a load means driven by a low pressure rotor of a gas turbine engine having a booster compressor drivenly connected to a low pressure turbine on said low pressure rotor;
- a core engine compressor downstream of said booster compressor along a core engine flowpath and drivenly connected to a high pressure turbine on a high pressure rotor;
- a variable bleed valve bleed apparatus for bleeding a portion of flow from said core engine flowpath, said variable bleed valve having a bleed passage opening along said core engine flowpath disposed between said booster compressor and core engine compressors;
- and
- a bleed door to close said bleed passage opening, said bleed door comprising a pivotal flow splitter having a leading edge and a means to pivot said bleed door and said leading edge about a point substantially aft of said leading edge and into said core engine flowpath.
A bleed apparatus for a gas turbine engine for bleeding flow from the core engine flowpath, said bleed apparatus comprising:
- a booster variable bleed valve (VBV) disposed between a booster and an engine core compressor in the engine core flowpath, said VBV including a VBV door;
- a bleed passage opening along the engine flowpath;
- said VBV door comprising a pivotal flow splitter having a leading edge to split off a portion of the flow in the core engine flowpath through said opening;
- and
- a means to pivot said VBV door about a point substantially aft of said leading edge such that said leading edge and said VBV door can be pivoted into the core engine flowpath.
An aircraft gas turbine engine comprising:
- a booster compressor drivenly connected to a low pressure turbine on a low pressure rotor;
- a core engine compressor downstream of said booster compressor along a core engine flowpath and drivenly connected to a high pressure turbine on a high pressure rotor;
- a variable bleed valve bleed apparatus for particle removal and bleeding flow having a bleed passage opening along the core engine flowpath disposed between said booster and core engine compressors;
- a bleed door to close said opening, said bleed door comprising a pivotal flow splitter having a leading edge;
- and
- a means to pivot said bleed door and leading edge about a point substantially aft of said leading edge and into said core engine flowpath.
Dependencies are inferred from the claim text.