Reverse flow engine architecture

Patent metadata

Field	Value
Publication number	US-11719247-B2
Application number	US-202117406216-A
Country	US
Kind code	B2
Filing date	Aug 19, 2021
Priority date	Dec 20, 2016
Publication date	Aug 8, 2023
Grant date	Aug 8, 2023

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 turboprop engine comprising:
a propeller;
a reduction gearbox (RGB) having an output drivingly connected to the propeller;
an engine core comprising a low pressure (LP) spool module and a high pressure (HP) spool module arranged sequentially in an axial direction along an engine centerline,
the LP spool module comprising:
an LP compressor and an LP turbine, the LP compressor disposed forward of the LP turbine and aft of the RGB relative to a travel direction of the engine, the LP turbine drivingly connected to both an input of the RGB and the LP compressor, the LP spool module further comprising an LP shaft projecting axially forwardly from the LP turbine along the engine centerline;

the HP spool module comprising:
an HP compressor in flow communication with the LP compressor via an external duct disposed outside of the engine core, and an HP turbine disposed forward of the HP compressor and aft of the LP turbine, the HP turbine drivingly connected to the HP compressor, the HP spool module further comprising an HP shaft extending axially along the engine centerline between the HP turbine and the HP compressor;

the LP spool module and the HP spool module axially 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; and

an accessory gearbox (AGB) mounted in-line along the engine centerline aft of the HP compressor,
wherein the LP shaft and the HP shaft are axially spaced-apart by an axial gap extending through the split plane P, and wherein the LP spool module further comprises an LP compressor shaft extending axially between the LP turbine and the LP compressor, the LP compressor shaft radially offset from the LP shaft and the engine centerline.

2. The reverse flow turboprop engine defined in claim 1 , wherein the LP compressor is offset from the engine centerline.

3. The reverse flow turboprop engine defined in claim 1 , wherein the LP turbine is drivingly connected to the LP compressor via a gear train, the gear train disposed aft of the LP compressor and offset relative to the engine centerline.

4. The reverse flow turboprop engine defined in claim 1 , wherein both the LP compressor shaft and the LP shaft are fully spaced forwardly from the split plane P.

5. The reverse flow turboprop engine defined in claim 1 , wherein the HP shaft is spaced aft from the split plane P.

6. The reverse flow turboprop engine defined in claim 1 , wherein the external duct extends from a forward end of the engine to a location aft of the HP compressor and forward of the AGB at an aft end of the engine.

7. The reverse flow turboprop engine defined in claim 1 , wherein the LP compressor shaft is disposed entirely forward of the HP shaft.

8. The reverse flow gas turbine engine defined in claim 1 , wherein an air cooler is connected to the external duct between an outlet of the LP compressor and an inlet of the HP compressor.

Assignees

• Pratt & Whitney Canada

Inventors

• Plante Ghislain
• Valois Patrick

Classifications

• F04D25/045 Primary

  the pump wheel carrying the fluid driving means, e.g. turbine blades · CPC title

• F01D5/06

  Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections {(F01D5/022, F01D5/023 take precedence)} · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D15/12

  Combinations with mechanical gearing (driven by multiple engines F01D13/00) · CPC title

• F02C3/145 Primary

  the combustion chamber being in the reverse flow-type · CPC title