Turboshaft gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorsKeith Morgan, Eric Durocher
Life of this patent
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Abstract
The turboshaft engine for a rotorcraft includes a low pressure spool having a low pressure compressor and a low pressure turbine section, and a high pressure spool having a high pressure compressor and a high pressure turbine section. The spools are independently rotatable relative to one another. The low pressure compressor section includes a mixed flow rotor. A set of variable guide vanes (VGVs) are discposed upstream of each of the low pressure and high pressure compressors, the VGVs being configured to be independently operable relative to one another.
Claims11
A turboshaft engine for a rotorcraft, the turboshaft gas turbine engine comprising:
- at least two spools independently rotatable relative to each other, a low pressure spool of the at least two spools including a low pressure shaft interconnecting a low pressure compressor section to a low pressure turbine section, and a high pressure spool of the at least two spools including a high pressure shaft interconnecting a high pressure compressor section to a high pressure turbine section, the low pressure compressor section including a mixed flow rotor, and the high pressure compressor includes a mixed flow rotor;
- and
- a first set of variable guide vanes disposed upstream of the low pressure compressor and a second set of variable guide vanes disposed upstream of the high pressure compressor, the first set of variable guide vanes being mechanically decoupled from the second set of variable guide vanes, whereby the first and second sets of variable guide vanes are independently operable relative to one another.
A turboshaft engine for a rotorcraft, the turboshaft gas turbine engine comprising:
- a low pressure spool having a low pressure compressor and a low pressure turbine section, the low pressure compressor section including a mixed flow rotor, a high pressure spool having a high pressure compressor and a high pressure turbine section, the high pressure compressor including a mixed flow rotor, the spools independently rotatable relative to one another, a set of variable guide vanes (VGVs) upstream of each of the low pressure and high pressure compressors, the VGVs configured to be independently operable relative to one another.
Dependencies are inferred from the claim text.