Patent ID: 7861536
Filing Date: 2011-01-04
Classification: F01D,F02C,F05D

Abstract:
1. A passive pressurizing air system for a gas turbine engine comprising: a flow path for directing an air flow having a first temperature and a first pressure from a pressure stage of a compressor of the engine to a pressurized area of the engine, the flow path extending through a cavity having a high pressure stage port therein, the high pressure stage port filled in the cavity with pressurized air from a different stage of the compressor having a second temperature and a second pressure greater than the respective first temperature and first pressure, the cavity being defined by a casing immediately surrounding a combustor of the engine; and an air flow mixing apparatus located within the cavity, the apparatus communicating with the flow path intermediate the pressure stage and pressurized area, the apparatus also communicating with the cavity for adding the pressurized air from the cavity into the flow path to provide a mixed air flow having a temperature and a pressure intermediate to the first and second temperatures and the first and second pressures, the mixed air flow flowing through a pipe that connected to the flow mixing apparatus inside the cavity to the components downstream of a turbine assembly.