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US 2014/0178174 A1Published application
Gas turbine engine including a pre-diffuser heat exchanger
AssigneeUnited Technologies Corporation
InventorsJoseph T. Caprario, Shawn J. Gregg, Dave J. Hyland
Life of this patent
Estimating the term…
Abstract
According to an example embodiment, a gas turbine engine assembly includes, among other things, a compressor. A strut near the compressor includes a flow passage through a portion of the strut. The flow passage is configured to direct air from the compressor to another portion of the gas turbine engine. The flow passage has at least one surface feature that at least partially hinders some airflow through the flow passage.
Claims22
A gas turbine engine assembly, comprising:
- a compressor (52);
- and
- a strut (100) near the compressor, the strut including a flow passage (102) through a portion of the strut, the flow passage being configured to direct air (104) from the compressor to another portion 54) of the gas turbine engine, the flow passage having at least one surface feature (120) that at least partially augments heat transfer within the flow passage.
A gas turbine engine assembly, comprising:
- a compressor (52);
- and
- a strut (100) near the compressor, the strut including a flow passage (102) through a portion of the strut, the flow passage being configured to direct air from the compressor (52) to another portion (54) of the gas turbine engine, the flow passage having at least one surface feature (120) that provides an increased surface area for contacting at least some airflow through the flow passage.
A method of operating a gas turbine engine, comprising the steps of:
- directing airflow from a compressor (52) into a flow passage (102) through a strut (100) near the compressor;
- at least partially reducing a temperature of the airflow (104, 106) in the flow passage;
- and
- directing (108) air from the flow passage toward a turbine portion (54) of the gas turbine engine.
1 more element
Dependencies are inferred from the claim text.