Compound engine assembly with offset turbine shaft, engine shaft and inlet duct

Patent metadata

Field	Value
Publication number	US-10677154-B2
Application number	US-201816164148-A
Country	US
Kind code	B2
Filing date	Oct 18, 2018
Priority date	Feb 20, 2015
Publication date	Jun 9, 2020
Grant date	Jun 9, 2020

Abstract

A compound engine assembly with an inlet duct, a compressor, an engine core including at least one internal combustion engine, and a turbine section including a turbine shaft configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft and the engine shaft are parallel to each other. The turbine shaft, the engine shaft and at least part of the inlet duct are all radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.

First claim

The invention claimed is:

1. A compound engine assembly comprising:
an inlet duct having a longitudinal central axis, an air flow within the inlet duct occurring along a direction corresponding to that of the longitudinal central axis;
a conduit communicating with the inlet duct;
a compressor having an inlet in fluid communication with the conduit, the compressor including at least one compressor rotor connected to a turbine shaft;
an engine core including at least one internal combustion engine in driving engagement with an engine shaft, the engine core having an inlet in fluid communication with an outlet of the compressor;
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 connected to the turbine shaft, the turbine shaft configured to compound power with the engine shaft;
wherein the turbine shaft and the engine shaft are parallel to each other; and
wherein the turbine shaft, the engine shaft and the longitudinal central axis of at least part of the inlet duct are all radially offset from one another, the at least part of the inlet duct including an inlet of the inlet duct in fluid communication with ambient air around the compound engine; wherein the longitudinal axis of at least part of the inlet duct is parallel to the turbine shaft and to the engine shaft, and wherein the engine assembly is a reversed flow assembly such that the inlet of the inlet duct is closer to the turbine section than to the compressor.

2. The compound engine assembly as defined in claim 1 , wherein the longitudinal central axis of a majority of the inlet duct is radially offset from the turbine shaft and from the engine shaft.

3. The compound engine assembly as defined in claim 1 , wherein the turbine shaft is connected to the engine shaft through a gearbox.

4. The compound engine assembly as defined in claim 3 , wherein the gearbox is located between the compressor and the turbine section.

5. The compound engine assembly as defined in claim 1 , wherein the compressor and the turbine section are respectively provided in a compressor module casing and in a turbine module casing, the compressor module and turbine module casings being spaced from one another and removable from the assembly independently from one another.

6. 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.

7. 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.

8. The compound engine assembly as defined in claim 7 , wherein the first stage turbine is configured as an impulse turbine with a pressure-based reaction ratio having a value of at most 0.2, the second stage turbine having a higher reaction ratio than that of the first stage turbine.

9. A compound engine assembly comprising:
an inlet duct having an inlet in fluid communication with ambient air around the compound engine assembly;
a compressor having an inlet in fluid communication with the inlet duct;
an engine core including at least one internal combustion engine in driving engagement with an engine shaft, the engine core having an inlet in fluid communication with an outlet of the compressor;
a turbine section including 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, each of the first stage turbine and the second stage turbine including at least one rotor connected to a turbine shaft, the turbine shaft and the engine shaft being in driving engagement with one another;
wherein the turbine shaft and the engine shaft are parallel to each other; and
wherein the turbine shaft, the engine shaft and at least part of the inlet duct are all radially offset from one another, the at least part of the inlet duct including an inlet of the inlet duct in fluid communication with ambient air around the compound engine assembly; wherein a longitudinal axis of at least part of the inlet duct is parallel to the turbine shaft and to the engine shaft, and wherein the engine assembly is a reversed flow assembly such that the inlet of the inlet duct is closer to the turbine section than to the compressor.

10. The compound engine assembly as defined in claim 9 , wherein a longitudinal central axis of at least part of the inlet duct is radially offset from the turbine shaft and from the engine shaft.

11. The compound engine assembly as defined in claim 9 , wherein the turbine shaft is connected to the engine shaft through a gearbox.

12. The compound engine assembly as defined in claim 11 , wherein the gearbox is located between the compressor and the turbine section.

13. The compound engine assembly as defined in claim 9 , wherein the compressor and the turbine section are respectively provided in a compressor module casing and in a turbine module casing, the compressor module and turbine module casings being separate from one another and removable from the assembly independently from one another.

14. The compound engine assembly as defined in claim 9 , 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.

15. The compound engine assembly as defined in claim 9 , wherein the first stage turbine and the second stage turbine have different reaction ratios.

16. The compound engine assembly as defined in claim 9 , wherein the first stage turbine is configured as an impulse turbine with a pressure-based reaction ratio having a value of at most 0.2, the second stage turbine having a higher reaction ratio than that of the first stage turbine.

17. A method of driving a rotatable load of an aircraft, the method comprising:
directing ambient air from outside of the compound engine assembly into the compound engine assembly through an inlet duct;
directing the air from the inlet duct to an inlet of a compressor;
directing compressed air from an outlet of a compressor to an inlet of at least one internal combustion engine of a compound engine assembly;
driving rotation of an engine shaft with the at least one combustion engine;
driving rotation of a turbine shaft of a turbine section of the compound engine assembly by circulating an exhaust of the at least one internal combustion engine to an inlet of the turbine section; and
compounding power from the turbine shaft with that of the engine shaft to drive the rotatable load;
wherein the turbine shaft and the engine shaft are parallel to each other and radially offset with respect to each other; and
wherein the air is ci

Assignees

• Pratt & Whitney Canada

Inventors

• Lamarre Sylvain
• Fontaine Mike
• Julien Andre
• Gaul Michael
• Thomassin Jean
• Mitrovic Lazar
• Medvedev Ilya
• Usikov Sergey
• Zolotov Andrey

Classifications

• F01C21/18

  Arrangements for admission or discharge of the working fluid, e.g. constructional features of the inlet or outlet · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · 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

• F05D2230/72

  Maintenance · CPC title

• F05D2250/312

  the axes being parallel to each other · CPC title