Patent ID: 8834108
Filing Date: 2014-09-16
Classification: B64D,F01D,F02K,F05D,Y02T

Abstract:
1. A running-gap control system of an aircraft gas turbine with a core engine, comprising: a turbine having a turbine casing and at least one blade row having a running gap to the turbine casing; a core-engine ventilation compartment enclosed by a fairing, the core-engine ventilation compartment surrounding the turbine casing, the fairing forming an inner wall of a bypass duct; a cooling air distributor positioned around the turbine casing for directing cooling air flow into the core-engine ventilation compartment to the turbine casing to control the running gap; at least one scoop type inlet nozzle projecting into and open to the bypass duct for directing bypass air from the bypass duct into the cooling air distributor, an inlet opening of the scoop type inlet separated from the fairing forming the inner wall of the bypass duct, all cooling air supplied to the cooling air distributor being supplied from the bypass duct; a control system for controlling an amount of bypass air from the bypass duct into the cooling air distributor; an outlet nozzle positioned in the bypass duct upstream of an engine nozzle to output the bypass air from the core-engine ventilation compartment beck into the bypass flow in the bypass duct in a direction of the bypass flow to provide thrust to the bypass flow, the system having an aerodynamic design between the inlet nozzle and the outlet nozzle to reduce pressure losses therebetween to permit the outlet nozzle to output the bypass air from the core-engine ventilation compartment back into the bypass flow in the bypass duct upstream of the engine nozzle; and a flow line connecting the core-engine ventilation compartment with the outlet nozzle to route the bypass air from the core-engine ventilation compartment to the outlet nozzle; the flow line being routed through at least one aerodynamic fairing positioned in the bypass duct.