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US 2019/0195127 A1Published application
Axial compressor with inter-stage centrifugal compressor
AssigneeUnited Technologies Corporation
InventorsMatthew E Bintz, Enzo DiBenedetto
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Abstract
An auxiliary compressor for a gas turbine engine is disclosed. The auxiliary compressor includes a first axial rotor, a second axial rotor positioned downstream of the first axial rotor, and a centrifugal impeller positioned intermediate the first axial rotor and the second axial rotor and operably coupled to the first axial rotor.
Claims20
A gas turbine engine, comprising:
- a first axial rotor;
- a second axial rotor positioned adjacent the first axial rotor;
- and
- a centrifugal compressor positioned axially intermediate the first axial rotor and the second axial rotor and operably coupled to the first axial rotor.
1 more element
An auxiliary compressor for a gas turbine engine, comprising:
- a first axial rotor;
- a second axial rotor positioned downstream of the first axial rotor;
- and
- a centrifugal impeller positioned intermediate the first axial rotor and the second axial rotor and operably coupled to the first axial rotor.
1 more element
A gas turbine engine, comprising:
- a high pressure axial compressor having a first axial rotor and a second axial rotor positioned downstream of the first axial rotor;
- and
- a centrifugal compressor positioned intermediate the first axial rotor and the second axial rotor and operably coupled to the first axial rotor.
Dependencies are inferred from the claim text.