Gas turbine engine

Abstract

The invention relates to a gas turbine engine. The gas turbine engine comprises an engine core comprising a compressor; a compressor bleed valve in communication with the compressor and configured torelease bleed air from the compressor; at least one component provided at the inlet of the engine core having a de-icing conduit, configured to receive the bleed air; and a flow controller, configuredto provide bleed air to the de-icing conduit of the at least one component in response to either or both of a requirement to de-ice the component and a requirement to release bleed air from the compressor to optimize operation of the core. The flow controller is configured to provide a first mass flow rate of bleed air when the bleed air is provided in response to a requirement to de-ice the component and a second mass flow rate of bleed air, different from the first mass flow rate, when the bleed air is provided in response to a requirement to release bleed air from the compressor to optimize operation of the core, and to provide the higher of the first and second mass flow rates of bleed air when the bleed air is required both for de-icing the component and to optimize operation of thecore.

Description

technical field [0001] The present disclosure relates to gas turbine engines, and in particular to gas turbine engines including a compressor bleed air valve for releasing bleed air from a compressor. Background technique [0002] Gas turbine engines may require compressor bleed valves to relieve pressure from compressor stages within the core of the gas turbine engine. In some gas turbine engines, compressor bleed air is discharged through an outlet in the outer casing of the core into the engine's bypass duct. In a typical arrangement, the compressor induction valve is located in the compressor casing (or inner core casing) and is piped to an orifice in the outer casing. Such arrangements require reinforced apertures, seals and sealing bands in the outer casing, all of which add weight to the gas turbine engine core. Also, venting the compressor bleed air into the bypass line may risk thermal damage to the nacelle and may generate additional noise. [0003] It is an obj...

AI Technical Summary

Problems solved by technology

Such arrangements require reinforced orifices in the outer casing, seals and sealing bands, all of which add weight to the gas turbine engine core

Also, venting the compressor bleed air into the bypass line may risk thermal damage to the nacelle and may create additional noise

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