Air intake for turboprop engine

Patent metadata

Field	Value
Publication number	US-10087839-B2
Application number	US-201615052214-A
Country	US
Kind code	B2
Filing date	Feb 24, 2016
Priority date	Feb 24, 2016
Publication date	Oct 2, 2018
Grant date	Oct 2, 2018

Abstract

An air intake for efficiently channeling a flow of ambient air toward an air inlet of a turboprop or turboshaft gas turbine engine is disclosed. The air intake comprises an intake inlet for receiving the flow of air, an intake duct for channelling the flow of air, and an intake outlet for discharging the flow of air toward the air inlet of the gas turbine engine. The intake duct may be oriented toward a flow direction of the air pushed aft by a propeller coupled to the gas turbine engine.

First claim

What is claimed is:

1. An air intake for a turboprop gas turbine engine of an aircraft, the air intake being configured to channel air pushed aft by a propeller coupled to the gas turbine engine toward an engine inlet of the turboprop gas turbine engine, the air intake having a reference axis that is substantially coaxial with a longitudinal axis of the gas turbine engine when the air intake is installed on the gas turbine engine, the air intake comprising:
an intake inlet for receiving a flow of air therein from the air pushed aft by the propeller, the intake inlet being configured to be generally forward-facing relative to the gas turbine engine and offset radially outwardly relative to the reference axis;
an intake duct in fluid communication with the intake inlet, the intake duct being configured to channel the flow of air received in the intake inlet, at least part of the intake duct adjacent the intake inlet extending along an intake axis that is non-parallel to the reference axis, the intake axis being oriented toward a predetermined flow direction of the air pushed aft by the propeller upstream of the intake inlet during operation of the gas turbine engine, the intake axis being at an angle (β 1 ) that is greater than 0 degree and less than 5 degrees from the reference axis measured in a horizontal plane relative to the installed orientation of the air intake on the gas turbine engine; and
an intake outlet in fluid communication with and downstream from the intake duct, the intake outlet being configured to discharge the flow of air toward the engine inlet.

2. The air intake as defined in claim 1 , wherein the intake axis is at an angle (β 2 ) that is greater than 0 degree and less than 30 degrees from the reference axis measured in a vertical plane extending along the reference axis and relative to the installed orientation of the air intake on the gas turbine engine.

3. The air intake as defined in claim 1 , wherein the intake axis is at an angle (β 2 ) of about 12 degrees from the reference axis measured in a vertical plane extending along the reference axis and relative to the installed orientation of the air intake on the gas turbine engine.

4. The air intake as defined in claim 1 , wherein the intake axis is substantially parallel to the predetermined flow direction of the air pushed aft by the propeller upstream of the intake inlet during at least one mode of operation of the gas turbine engine.

5. The air intake as defined in claim 1 , comprising a scroll portion in fluid communication with the intake duct, the scroll portion being configured to receive the flow of air from the intake duct and channel the flow of air toward the intake outlet, the scroll portion comprising:
a first scroll branch disposed on one side of the reference axis and a second scroll branch disposed on another side of the reference axis, the first scroll branch and the second scroll branch merging together at a location diametrically opposed to the intake duct relative to the reference axis; and
a flow separator disposed substantially at the merging location of the first scroll branch and the second scroll branch.

6. The air intake as defined in claim 1 , wherein the intake duct has a first internal cross-sectional area at a first location proximal to the intake inlet and a second internal cross-section area at a second location downstream of the first location and along the intake axis, a ratio of the second internal cross-section area over the first internal cross-sectional area being less than 2.0.

7. The air intake as defined in claim 6 , wherein the intake duct has a cross-sectional profile at the second location downstream of the first location that is kidney-shaped.

8. The air intake as defined in claim 7 , wherein the intake inlet has a cross-sectional profile that is kidney-shaped.

Assignees

• Pratt & Whitney Canada

Inventors

• Gekht Eugene
• Bisson Francois
• Cunningham Mark
• Desjardins Michel
• YAN Guo Rong

Classifications

• F02K3/02 Primary

  in which part of the working fluid by-passes the turbine and combustion chamber · CPC title

• B64D2033/022

  comprising bird or foreign object protections · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• B64D2033/0293

  for turboprop engines · CPC title

• B64D2033/0246

  comprising particle separators · CPC title