Turbocooled vane of a gas turbine engine
AssigneePowerphase LLC
InventorsRobert J. KRAFT, Peter PERRI
Life of this patent
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Abstract
The present invention discloses a novel apparatus and methods for providing a flow of cooling air to one or more turbine nozzles or turbine blade outer air seals. The flow of cooling air is provided by an external source and regulated in order to improve turbine nozzle and air seal cooling efficiency and component life.
Claims18
A method of cooling a turbine nozzle in a gas turbine engine, the gas turbine engine having a compressor section, a compressor discharge plenum, a combustor section, and a turbine section fluidly connected to each other, the method comprising:
- compressing a portion of a cooling air for the turbine nozzle through a separate process external to the gas turbine engine to form a supply of compressed air;
- directing the supply of compressed air to a leading edge of the turbine nozzle for backside cooling of the leading edge;
- and,
- directing a portion of the supply of compressed air from the leading edge to a portion of the turbine nozzle aft of the leading edge.
A method of cooling a turbine nozzle in a gas turbine engine, the gas turbine engine having a compressor section, a compressor discharge plenum, a combustor section, and a turbine section fluidly connected to each other, the method comprising:
- compressing at least a portion of a cooling air for the turbine nozzle using a fueled engine and a fueled engine compressor external to the gas turbine engine to form a supply of compressed air;
- directing the supply of compressed air to a leading edge of the turbine nozzle for backside cooling of the turbine nozzle;
- and,
- directing a portion of the supply of compressed air from the leading edge to a portion of the turbine nozzle aft of the leading edge.
A method of cooling a turbine nozzle in a gas turbine engine, the gas turbine engine having a compressor section, a compressor discharge plenum, a combustor section, and a turbine section fluidly connected to each other, the method comprising:
- compressing a portion of a cooling air for the turbine nozzle using a separate process comprising a fueled engine and a fueled engine compressor external to the gas turbine engine to form a supply of compressed air having a pressure above a pressure of air in the compressor discharge plenum;
- directing the supply of compressed air to a leading edge of the turbine nozzle for backside cooling of the turbine nozzle;
- and,
- directing a portion of the supply of compressed air from the leading edge to a portion of the turbine nozzle aft of the leading edge.
Dependencies are inferred from the claim text.