Turboshaft gas turbine engine

Patent metadata

Field	Value
Publication number	US-11536153-B2
Application number	US-201916535397-A
Country	US
Kind code	B2
Filing date	Aug 8, 2019
Priority date	Aug 8, 2018
Publication date	Dec 27, 2022
Grant date	Dec 27, 2022

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.

First claim

The invention claimed is:

1. 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.

2. The turboshaft engine as defined in claim 1 , wherein the first set of variable guide vanes is operable between an 80 degree position and a −25 degree position associated with the first set of variable guide vanes.

3. The turboshaft engine as defined in claim 2 , wherein the second set of variable guide vanes is operable between an 80 degree position and a −25 degree position associated with the second set of variable guide vanes.

4. The turboshaft engine as defined in claim 1 , wherein the first set of variable guide vanes is operable between an 80 degree position and a −25 degree position associated with the first set of variable guide vanes while the second set of variable guide vanes is maintained in a given position.

5. The turboshaft engine as defined in claim 1 , wherein the high pressure turbine section includes only a single turbine stage.

6. The turboshaft engine as defined in claim 5 , further comprising an intermediate spool including an intermediate pressure compressor and an intermediate pressure turbine, and a third set of variable guide vanes disposed at an inlet of the intermediate pressure compressor, the third set of variable guide vanes operable independently of the other two sets of variable guide vanes.

7. The turboshaft engine as defined in claim 1 , wherein low pressure compressor includes only a single mixed flow rotor.

8. 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.

9. The turboshaft engine as defined in claim 8 , wherein the low pressure compressor includes only a single mixed flow rotor.

10. The turboshaft engine as defined in claim 8 , wherein at least one set of the variable guide vanes is operable between an +80 degree position and a −25 degree position.

11. The turboshaft engine as defined in claim 10 , wherein the low pressure compressor variable guide vanes are operable between the +80 degree position and the −25 degree position.

Assignees

• Pratt & Whitney Canada

Inventors

• Morgan Keith
• Durocher Eric

Classifications

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F01D13/003 Primary

  with at least two independent shafts, i.e. cross-compound · CPC title

• B64D31/00

  Power plant control systems; Arrangement of power plant control systems in aircraft · CPC title

• F02C6/02 Primary

  Plural gas-turbine plants having a common power output · CPC title

• F02C9/54

  by throttling the working fluid, by adjusting vanes · CPC title