Patent ID: 8683811
Filing Date: 2014-04-01
Classification: F02C,F04D,F05D,Y02T

Abstract:
1. A method for operating an aero jet engine with compressor air circulation for stabilizing flow conditions, comprising: identifying a highly loaded, surge-prone compressor stage of the jet engine; tapping a compressor bleed air at a bleed point at a compressor stage downstream of the surge-prone compressor stage and routing the tapped compressor bleed air through a heat exchanger to cool the tapped compressor bleed air, the tapped compressor bleed air having a higher pressure than a pressure at the surge-prone compressor stage; reducing surge at the surge-prone compressor stage with the higher pressure bleed air by feeding the tapped higher pressure compressor bleed air through a bleed air line to the surge-prone upstream compressor stage; providing the jet engine with a bypass duct for flowing bypass air that is cooler than the tapped compressor bleed air; positioning the heat exchanger in the bypass duct to be in contact with the cooler bypass air to cool the tapped compressor bleed air prior to the tapped compressor bleed air reentering the compressor through the bleed air line such that a temperature of the cooled compressor bleed air reentering the compressor is lower than a temperature of compressor air at a position of reentering; wherein the compressor air flows in an axial direction from the surge prone compressor stage to the bleed point compressor stage and wherein the heat exchanger is positioned axially between the two stages; feeding the cooled compressor bleed air from the bleed air line at a feed position onto tips of rotor blades of the surge-prone compressor stage to simultaneously cool the tips of the rotor blades while reducing the surge at the surge-prone compressor stage; the upstream compressor stage being a separate compressor stage than the downstream compressor stage with the bleed point being separated from the feed position by at least one stator row; the routing of the bleed air from the bleed point through the bypass duct to the feed position bypassing and separate from a turbine stage of the engine.