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

a technology of compound engine and offset turbine shaft, which is applied in the direction of combination engine, machine/engine, transportation and packaging, etc., can solve the problem of difficulty in adapting to aircraft applications

Inactive Publication Date: 2016-08-25
PRATT & WHITNEY CANADA CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Compound engine assemblies including a compressor used as a supercharger or turbocharger may define a relatively bulky assembly w...

Method used

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

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Embodiment Construction

[0020]Referring to FIG. 1, a compound engine assembly 10 is generally shown, including a liquid cooled heavy fueled multi-rotor rotary engine core 12. The engine core 12 has an engine shaft 16 driven by the engine core 12 and driving a rotatable load, which is shown here as a drive shaft 8. The drive shaft 8 may be an integral part of the engine shaft 16, be directly connected thereto, or be connected thereto through a gearbox (not shown). It is understood that the compound engine assembly 10 may alternately be configured to drive any other appropriate type of load, including, but not limited to, one or more generator(s), propeller(s), accessory(ies), rotor mast(s), compressor(s), or any other appropriate type of load or combination thereof.

[0021]The compound engine assembly 10 is configured as a single shaft engine. The term “single shaft” is intended herein to describe a compound engine where all the rotating components (compressor rotor(s), turbine rotor(s), engine shaft, accesso...

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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.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS[0001]This application claims priority from U.S. provisional application No. 62 / 118,914 filed Feb. 20, 2015, the entire contents of which are incorporated by reference herein.TECHNICAL FIELD[0002]The application relates generally to compound engine assemblies and, more particularly, to supercharged or turbocharged compound engine assemblies used in aircraft.BACKGROUND OF THE ART[0003]Compound engine assemblies including a compressor used as a supercharger or turbocharger may define a relatively bulky assembly which may be difficult to fit into existing aircraft nacelles, thus creating some difficulty in adapting them for aircraft applications.SUMMARY[0004]In one aspect, there is provided 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, the compressor including at least one comp...

Claims

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Application Information

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IPC IPC(8): F02B41/00F01C11/00F02C7/36F01C21/18F01C1/22
CPCF01C21/18F05D2250/312F05B2220/40F05D2220/323F05D2300/171B64D27/06F01C1/22F01C11/008F02C6/12F02C6/206F02C7/052F02C7/36B64D2700/62947F05D2230/51F05D2230/72F05D2260/4031F05D2300/121F02B41/00Y02T10/12
Inventor LAMARRE, SYLVAINFONTAINE, MIKEJULIEN, ANDREGAUL, MICHAELTHOMASSIN, JEANMITROVIC, LAZARMEDVEDEV, ILYA B.USIKOV, SERGEYZOLOTOV, ANDREY
Owner PRATT & WHITNEY CANADA CORP
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