Compound engine assembly with coaxial compressor and offset turbine section

Patent metadata

Field	Value
Publication number	US-2016245166-A1
Application number	US-201514806880-A
Country	US
Kind code	A1
Filing date	Jul 23, 2015
Priority date	Feb 20, 2015
Publication date	Aug 25, 2016
Grant date	—

Abstract

A compound engine assembly having an engine core including at least one internal combustion engine in driving engagement with an engine shaft, a compressor having an outlet in fluid communication with an inlet of the engine core and including at least one rotor rotatable about an axis coaxial with the engine shaft, the engine shaft in driving engagement with the compressor rotor, and a turbine section having an inlet in fluid communication with an outlet of the engine core and including at least one rotor engaged on a rotatable turbine shaft, the turbine shaft configured to compound power with the engine shaft. The turbine and engine shafts are parallel to and radially offset from one another, and the turbine shaft and the axis of the compressor rotor are parallel to and radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.

First claim

1 . A compound engine assembly comprising:
an engine core including at least one internal combustion engine in driving engagement with an engine shaft; a compressor having an outlet in fluid communication with an inlet of the engine core, the compressor including at least one compressor rotor rotatable about an axis of rotation coaxial with the engine shaft, the engine shaft in driving engagement with the compressor rotor; and a turbine section having an inlet in fluid communication with an outlet of the engine core, the turbine section including at least one turbine rotor engaged on a rotatable turbine shaft, the turbine shaft configured to compound power with the engine shaft, the turbine and engine shafts being parallel to one another and radially offset from one another, the turbine shaft and the axis of rotation of the compressor rotor being parallel to one another and radially offset from one another.

2 . The compound engine assembly as defined in claim 1 , wherein each of the at least one internal combustion engine includes a rotor sealingly and rotationally received within a respective internal cavity to provide rotating chambers of variable volume in the respective internal cavity, the rotor having three apex portions separating the rotating chambers and mounted for eccentric revolutions within the respective internal cavity, the respective internal cavity having an epitrochoid shape with two lobes.

3 . The compound engine assembly as defined in claim 1 , wherein the turbine shaft and the engine shaft are drivingly engaged to a rotatable load through a same gearbox.

4 . The compound engine assembly as defined in claim 3 , wherein the same gearbox includes an offset gear train mechanically linking the turbine shaft and the engine shaft and a planetary gear system mechanically linking the engine shaft and the rotatable load.

5 . The compound engine assembly as defined in claim 4 , wherein the rotatable load is a propeller.

6 . The compound engine assembly as defined in claim 1 , wherein the turbine section includes a first stage turbine having an inlet in fluid communication with the outlet of the engine core, and a second stage turbine having an inlet in fluid communication with an outlet of the first stage turbine.

7 . The compound engine assembly as defined in claim 6 , wherein the first stage turbine is configured as an impulse turbine with a pressure-based reaction ratio having a value of at most 0.25, the second stage turbine having a higher reaction ratio than that of the first stage turbine.

8 . The compound engine assembly as defined in claim 1 , wherein the at least one rotor of the compressor is engaged on a rotatable compressor shaft coaxial to the engine shaft, the engine shaft in driving engagement with the compressor shaft through a planetary gear system.

9 . The compound engine assembly as defined in claim 8 , wherein a sun gear of the planetary gear system is provided on the compressor shaft, a planet gear carrier of the planetary gear system is connected to the engine shaft, and a ring gear of the planetary gear system is fixed.

10 . The compound engine assembly as defined in claim 1 , wherein the turbine section is enclosed in a casing separate from that of the engine core and the compressor, the turbine section being modular and removable from the assembly.

11 . A compound engine assembly comprising:
an engine core including at least one internal combustion engine in driving engagement with an engine shaft; a compressor having an outlet in fluid communication with an inlet of the engine core, the compressor including at least one compressor rotor engaged on a rotatable compressor shaft, the engine shaft extending coaxially to the compressor shaft and being in driving engagement therewith; and a turbine section having a rotatable turbine shaft configured to compound power with the engine shaft, a first stage turbine having at least one first stage turbine rotor engaged to the turbine shaft and an inlet in fluid communication with an outlet of the engine core, and a second stage turbine having at least one second stage turbine rotor engaged to the turbine shaft and an inlet in fluid communication with an outlet of the first stage turbine, the turbine and engine shafts being parallel to one another and non-coaxial, the turbine and compressor shafts being parallel to one another and non-coaxial.

12 . The compound engine assembly as defined in claim 11 , wherein the turbine shaft and the engine shaft are drivingly engaged to a rotatable load through a same gearbox.

13 . The compound engine assembly as defined in claim 12 , wherein the same gearbox includes an offset gear train mechanically linking the turbine shaft and the engine shaft and a planetary gear system mechanically linking the engine shaft and the rotatable load.

14 . The compound engine assembly as defined in claim 13 , wherein the rotatable load is a propeller.

15 . The compound engine assembly as defined in claim 11 , wherein the first stage turbine and the second stage turbine have different reaction ratios.

16 . The compound engine assembly as defined in claim 15 , wherein the first stage turbine is configured as an impulse turbine with a pressure-based reaction ratio having a value of at most 0.25, the reaction ratio of the second stage turbine being higher reaction ratio than that of the first stage turbine.

17 . The compound engine assembly as defined in claim 11 , wherein the engine shaft is in driving engagement with the compressor shaft through a planetary gearbox.

Assignees

• Pratt & Whitney Canada

Inventors

• Thomassin Jean
• Bolduc Sebastien
• Villeneuve Bruno
• Berube Stephane
• Fontaine Mike
• Gagnon-Martin David
• Bilodeau Jade
• Julien Andre
• Legare Pierre-Yves
• Nichols Jason

Classifications

• F02B39/04

  Mechanical drives; Variable-gear-ratio drives (non-mechanical pump drives having variable gear ratio F02B39/08) · CPC title

• F05D2260/98

  Lubrication · CPC title

• F01C1/22

  of internal-axis type with equidirectional movement of co-operating members at the points of engagement, or with one of the co-operating members being stationary, the inner member having more teeth or tooth- equivalents than the outer member · CPC title

• F02C7/055

  with intake grids, screens or guards · CPC title

• F02B33/40

  of non-positive-displacement type · CPC title