Gas turbine engine with inertial particle separator

Patent metadata

Field	Value
Publication number	US-11066996-B2
Application number	US-201816202827-A
Country	US
Kind code	B2
Filing date	Nov 28, 2018
Priority date	Apr 27, 2018
Publication date	Jul 20, 2021
Grant date	Jul 20, 2021

Abstract

There is disclosed an inertial particle separator communicating with an engine inlet. The inertial particle separator has: a main duct body; a bypass duct; and a splitter defined by an intersection of the main duct and the bypass duct. The main duct and the bypass duct having particular geometric characteristics. A method of separating particles via inertia in an aircraft engine inlet is also provided.

First claim

The invention claimed is:

1. An inertial particle separator configured for communicating with an engine inlet of an aircraft engine having an axis, the inertial particle separator comprising:
a main duct having an inlet fluidly connected to an environment outside of the aircraft engine and an outlet configured for being fluidly connected to the engine inlet, the main duct having a first side facing away from the axis and a second side opposed to the first side and facing toward the axis, the inlet for receiving an airflow from the environment along a first direction;
a bypass duct stemming from the main duct between the inlet and the outlet, the bypass duct being fluidly connected to the main duct; and
a splitter defined by an intersection of the main duct and the bypass duct, the splitter having a leading edge,
wherein the second side of the main duct at the inlet extends from the inlet along a second direction defining an angle (α) of at most 45 degrees with the first direction,
wherein, the main duct has a radially outward-most section between the inlet and the splitter, the radially-outward most section having a height (H 1 ) extending from the first side to the second side and a width (W 1 ), wherein W 1 /H 1 ≥0.5, the second side of the main duct free of a step at the radially-outward-most section,
wherein a length (G 1 ) from the second side to the first side and from the radially-outward most section along a direction parallel to the second direction is at least as great as the height (H 1 ) of the main duct at the radially outward-most section,
wherein a height (H 2 ) of the main duct from the leading edge of the splitter and the second side of the main duct is at most four times the height (H 1 ) of the main duct at the radially outward-most section, and
wherein a height (S 1 ) of the bypass duct from the first side at an end of the length (G 1 ) to the leading edge is at least 20% of the height (H 1 ) of the main duct at the radially outward-most section.

2. The inertial particle separator of claim 1 , wherein an upstream end of the splitter is rounded and has a diameter of at least 0.15 inch.

3. The inertial particle separator of claim 1 , wherein the splitter has a mid-plane located between the main duct and the bypass duct, a splitter angle (β) being defined between the mid-plane and the first direction is at least −60 degrees and at most 60 degrees.

4. The inertial particle separator of claim 3 , wherein the splitter angle is at least −30 degrees and at most 30 degrees.

5. The inertial particle separator of claim 1 , wherein the main duct at the radially outward-most section is substantially rectangular in cross-section.

6. The inertial particle separator of claim 1 , wherein the first side and the second side of the main duct at the radially outward-most section are curved.

7. The inertial particle separator of claim 1 , wherein G 1 /H 1 ≥2.

8. The inertial particle separator of claim 1 , wherein the angle (α) is at least 0 degree and at most 20 degrees.

9. The inertial particle separator engine of claim 1 , wherein the main duct separates into two sub-ducts extending away from one another in a circumferential direction relative to a central axis of the aircraft engine, each of the two sub-ducts connected to the engine inlet, the bypass duct extending from a point where the main duct separates in the two sub-ducts, the bypass duct extending between the two sub-ducts.

10. The inertial particle separator of claim 1 , wherein H 2 /H 1 ≤2, and wherein the main duct has a second length (L 1 ) from the inlet to the radially outward-most section along the first direction, wherein L 1 /H 1 ≥0.5.

11. An aircraft engine having an inertial particle separator communicating with an engine inlet of the aircraft engine, the inertial particle separator comprising:
a main duct having an inlet fluidly connected to an environment outside of the turboprop or turboshaft gas turbine engine and an outlet configured for being fluidly connected to the engine inlet, the main duct having an inner main duct wall and an outer main duct wall spaced apart from the inner main duct wall;
a bypass duct stemming from the main duct between the inlet and the outlet, the main duct being fluidly connected to the main duct, the bypass duct having an inner bypass duct wall and an outer bypass duct wall; and
a splitter defined by an intersection of the outer main duct wall and the inner bypass duct wall, the splitter having a leading edge,
wherein the main duct has a first segment, a second segment, and a third segment in serial flow communication, the first segment and the second segment being located upstream of the splitter relative to a flow of air through the main duct, the bypass duct located in the third segment,
wherein, at an upstream end of the first segment, an angle (α) between the inner main duct wall and a reference line defined by a direction of an airflow entering the main duct ranges from 0 to 45 degrees,
wherein, a cross-section of the main duct taken in a plane perpendicularly intersecting the reference line and located at an interface between the first segment and the second segment is characterized by a height (H 1 ) and a width (W 1 ), wherein W 1 /H 1 ≥0.5, the inner main duct wall free of a step at the interface between the first segment and the second segment,
wherein a length (G 1 ) of the second segment is defined from a first point located on the inner main duct wall at the interface between the first segment and the second segment and a second point located on the outer main duct wall, the length taken along a direction parallel to the inner main duct wall at the upstream end of the first segment, wherein G 1 /H 1 ≥1.0;
wherein a height (H 2 ) of the main duct at the third segment is defined between the leading edge and the inner main duct wall, the height (H 2 ) extending perpendicularly to both of the splitter to the inner main duct wall, wherein H 2 /H 1 ≤4,
wherein a height (S 1 ) of the bypass duct is defined from the second point and the leading edge of the splitter, wherein S 1 /H 1 ≥0.2.

12. The turboshaft or turboprop gas turbine engine of claim 11 , wherein an upstream end of the splitter is rounded and as a diameter of at least 0.15 inch.

13. The turboshaft or turboprop gas turbine engine of claim 11 , wherein the splitter has a mid-plane located between the outer main duct wall and the inner bypass duct wall, a splitter angle (β) being defined between the mid-plane and the reference line is at least −60 degrees and at most 60 degrees.

14. The turboshaft or turboprop gas turbine engine of claim 11 , wherein the main duct separates into two sub-ducts extending away from one another in a circumferential direction relative to a central axis of the aircraft engine, each of the two sub-ducts connected to the engine inlet, the bypass duct extending from a point where the main duct separates in the two sub-ducts, the bypass duct extending between the two sub-ducts.

15. The turboshaft or turboprop gas turbine engine of claim 11 , wherein the cross-section between the first segment and the second segment has a rectangular shape.

16. The turboshaft or turboprop gas turbine engine of claim 11 , wherein G 1 /H 1 ≥2.

17. The turboshaft or turboprop gas turbine engine of claim 11 , wherein the first segment has a length (L 1 ) taken along an axis parallel the reference line, wherein L 1 /H 1 ≥0.5.

18. A method of separating particles in an engine inlet of an aircraft engine, comprising:
receiving a flow of ambient air in an incoming direction from an

Assignees

• Pratt & Whitney Canada

Inventors

• Marrano Roberto
• Bisson Francois

Classifications

• B64D2033/0246

  comprising particle separators · CPC title

• F02K3/02

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

• F02C7/052 Primary

  with dust-separation devices · CPC title

• F02C7/04

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