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US 2014/0271121 A1Published application
Gas turbine engine architecture with intercooled twin centrifugal compressor
AssigneeUnited Technologies Corporation
InventorDaniel B. Kupratis
Life of this patent
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Abstract
A gas turbine engine includes an intercooled twin centrifugal compressor. A pipe diffuser extends from the intercooled twin centrifugal compressor into an airflow path.
Claims20
A gas turbine engine comprising:
- an intercooled twin centrifugal compressor;
- and
- a pipe diffuser that extends from said intercooled twin centrifugal compressor into an airflow path.
The gas turbine engine as recited in claim 11, wherein said full annular duct communicates with a high pressure compressor.
A method of operating a gas turbine engine comprising:
- extending a pipe diffuser from an intercooled twin centrifugal compressor into an airflow path.
Dependencies are inferred from the claim text.