Patent ID: 6634176
Filing Date: 2003-10-21
Classification: F01D,F02C,F05D

Abstract:
A turbine engine, comprising:a turbine rotationally driven by hot gas to exhaust the gas; a compressor rotationally coupled to the turbine to generate compressed air; an annular combustor for combusting fuel and the compressed air to generate the hot gas, the combustor extending coaxially away from the turbine to form a passage for the turbine exhaust gas therethrough; an annular recuperator surrounding the turbine for transferring heat from the turbine exhaust gas to the compressed air; a surface spaced from combustor to direct the exhaust gas exiting from the passage into the recuperator; and an elongated structure extending from the surface into the passage toward the turbine to direct the exhaust gas flowing through the exhaust passage, wherein the structure extends through the passage to terminate proximal to the turbine.