Regenerative turbine blade and vane cooling for a tip turbine engine
A fan-turbine rotor assembly ( 24 ) includes a multitude of turbine blades ( 34 ) which each define a turbine blade passage which bleed air from a diffuser section ( 74 ) to provide for regenerative cooling. Regenerative cooling airflow is communicated from the radial core airflow passage ( 80 ) through the diffuser passages ( 144 ), through diffuser aspiration passages ( 146 A, 146 B) and into the turbine blade passages ( 150 a ). The regenerative cooling airflow exits from the turbine blade passage ( 150 a ) and transfers received thermal energy into an annular combustor ( 30 ). The received thermal energy is recovered at the highest temperature in the cycle.
1. A method of regenerative cooling of a tip turbine engine comprising:
locating a turbine blade that extends from a fan blade downstream of a discharge flow from an annular combustor;
locating a turbine stator downstream of a discharge flow from the annular combustor;
communicating a regenerative cooling airflow through a turbine stator passage in the turbine stator; and
communicating the regenerative cooling airflow from the turbine stator passage into the annular combustor through a static structure flow passage subsequent to communicating the regenerative cooling airflow the turbine stator passage, the static structure flow passage having an axial component generally parallel to an axis of rotation of the fan blade.
2. A tip turbine engine comprising:
a compressor for compressing a core airflow;
a fan for accelerating bypass airflow and having a core airflow passage that receives said core airflow from said compressor;
an annular combustor for introducing fuel and combusting said core airflow from said fan; and
a turbine for extracting energy from said core airflow exiting said annular combustor, said turbine having at least one stage defined by a turbine blade that extends from a fan blade and a turbine vane, wherein said vane has a vane passage to receive a regenerative cooling airflow portion of said core airflow from said fan, said regenerative cooling portion of said core airflow exiting said vane passage for communication to said annular combustor, said regenerative cooling airflow portion of said core airflow is communicated through a turbine blade passage of said turbine blade prior to communication through said turbine vane passage.
3. The tip turbine engine as recited in claim 2 , wherein a static structure flow passage communicates the regenerative cooling airflow within said static structure flow passage in a direction generally opposite a bypass airflow generated by said fan blade section.
4. A method as recited in claim 1 , wherein communicating the regenerative cooling airflow from the turbine stator passage into the annular combustor in a direction generally opposite a propulsive airflow generated by the fan blade.