Reverse flow engine architecture

Patent metadata

Field	Value
Publication number	US-11125239-B2
Application number	US-201916717268-A
Country	US
Kind code	B2
Filing date	Dec 17, 2019
Priority date	Dec 20, 2016
Publication date	Sep 21, 2021
Grant date	Sep 21, 2021

Abstract

A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.

First claim

The invention claimed is:

1. A reverse flow turboshaft or turboprop engine comprising: a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction, the LP spool comprising an LP compressor drivingly connected to an LP turbine via an LP compressor gear train, the LP turbine separately drivingly connected to an external rotatable load via a reduction gearbox (RGB); the HP spool comprising an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and aft of the LP turbine, the HP turbine being drivingly connected to the HP compressor via an HP shaft, wherein the LP spool and the HP spool are disposed on opposed sides of an engine split plane (P) extending between the LP turbine and the HP turbine, the split plane (P) including a flange assembly for allowing the engine to be split between the LP turbine and the HP turbine, wherein the HP shaft is axially spaced from the engine split plane (P), and wherein the LP turbine is mounted for rotation about an engine centerline, and wherein LP compressor is offset from the engine centerline.

2. The reverse flow turboshaft or turboprop engine defined in claim 1 , wherein the LP spool further comprises an LP compressor shaft drivingly connected to the LP compressor gear train, and wherein the LP compressor shaft is disposed entirely forward of the HP shaft and of the engine split plane.

3. The reverse flow turboshaft or turboprop engine defined in claim 2 , wherein the LP spool further comprises an LP turbine shaft drivingly connected to the reduction gearbox (RGB), the RGB having an output shaft adapted to be connected to the external rotatable load.

4. The reverse flow turboshaft or turboprop engine defined in claim 3 , wherein the LP compressor shaft is parallel to the LP turbine shaft, and wherein both shafts extend forward of the LP turbine.

5. The reverse flow turboshaft or turboprop engine defined in claim 3 , wherein the LP compressor shaft branches off at an angle from the LP turbine shaft.

6. The reverse flow turboshaft or turboprop engine defined in claim 5 , wherein the LP compressor is non-coaxially disposed with respect to the LP turbine.

7. The reverse flow gas turboshaft or turboprop engine defined in claim 1 , wherein the LP spool and the HP spool respectively form part of an LP spool module and an HP spool module, the LP spool module being detachable from the HP spool module at the flange assembly (F).

8. The reverse flow turboshaft or turboprop engine defined in claim 1 , wherein the HP compressor is connected in fluid communication with the LP compressor via an external duct line disposed radially outside of a core of the engine.

9. The reverse flow turboshaft or turboprop engine defined in claim 8 , wherein an air cooler is mounted to the duct line.

Assignees

• Pratt & Whitney Canada

Inventors

• Plante Ghislain
• Valois Patrick

Classifications

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F02C6/206

  the vehicles being airscrew driven · CPC title

• F05D2250/313

  the axes being perpendicular to each other · CPC title

• F05D2250/312

  the axes being parallel to each other · CPC title

• F05D2240/60

  Shafts · CPC title