Patent ID: 8302407
Filing Date: 2012-11-06
Classification: F01D,F02C,F05D

Abstract:
1. A method for reducing temperature variation of a pressurized air supply to a pressurized area of a gas turbine engine, comprising: directing a first air flow having a low temperature thereof from a low pressure source of air associated with the gas turbine engine to the pressurized area of the gas turbine engine through an air flow mixing apparatus within a cavity defined by a core casing immediately surrounding a combustor, the cavity having a high pressure stage port therein; filling the cavity through the high pressure stage port with a second air flow having a high temperature from a high pressure source of air associated with the gas turbine engine; and adding the second air flow in the air flow mixing apparatus to provide a mixed pressurized air supply having an intermediate temperature thereof, to the pressurized area of the gas turbine engine via a supply pipe connected to the air flow mixing apparatus in a manner in which a ratio of energy distributed by the added second air flow in the mixed pressurized air supply varies to compensate for variations in the first air flow, thereby reducing variations in the intermediate temperature of the mixed pressurized air supply when the low temperature of the first air flow varies.