Turbine engine with particle deflector assembly

Abstract

A turbine engine includes an engine plenum disposed within the turbine engine and at least partially defined by plenum end walls and a turbocharger engine disposed within the engine plenum. A turbine engine flows core air through an engine plenum and into a turbocharger engine. A particle deflector assembly is disposed at the plenum end wall. The particle deflector assembly includes one or more particle deflector walls that extend into the engine plenum and capture particles within the core air.

Description

Technical Field

[0001] The present disclosure relates generally to turbine engines, and in particular to turboprop engines. Background Art

[0002] A turbine engine, in particular a turboprop engine, generally comprises a propeller and a core section arranged in flow communication with each other. The core section comprises a compressor, a combustor and a turbine section. A reverse flow turboprop engine comprises an engine air chamber in which the core section is arranged. BRIEF DESCRIPTION OF THE DRAWINGS

[0003] The foregoing and other features and advantages will become apparent from the following more particular description of various exemplary embodiments as illustrated in the accompanying drawings, in which like reference numerals generally indicate identical, functionally similar, or structurally similar elements.

[0004] Figure 1A is a schematic partial cross-sectional view of a turbine engine according to the present disclosure.

[0005] Figure 1B According to the present disclosure, Figure 1A Schematic partial sectional view of an aircraft with a turbine engine.

[0006] Figure 1C is a longitudinal centerline axis of the turbine engine according to the present disclosure and Figure 1B A schematic cross-sectional view of a portion of an engine plenum of a turbine engine including a particle deflector assembly, taken at detail 1C in FIG.

[0007] Figure 2A is a schematic cross-sectional illustration of a particle deflector assembly for the turbine engine of FIG. 1 , taken along a longitudinal centerline axis of the particle deflector assembly, according to another embodiment.

[0008] Figure 2B A schematic diagram of a device isolated from a turbine engine according to the present disclosure is shown. Figure 2A Part of a particle deflector assembly.

[0009] Figure 3 is a schematic cross-sectional illustration of a particle deflector assembly for the turbine engine of FIG. 1 , taken along a longitudinal centerline axis of the particle deflector assembly, according to another embodiment. DETAILED DESCRIPTION

[0010] Features, advantages and embodiments of the present disclosure are set forth or apparent by considering the following detailed description, drawings and claims.In addition, the following detailed description is exemplary and is intended to provide further explanation without limiting the scope of the present disclosure as claimed.

[0011] Various embodiments of the present disclosure are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

[0012] As used herein, the terms “first” and “second” may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of each component.

[0013] The terms "upstream" and "downstream" refer to the relative directions of the flow of a fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction to which the fluid is flowing.

[0014] The terms "fore" and "aft" refer to relative positions within a turbine engine or vehicle and refer to the normal operating attitude of the turbine engine or vehicle relative to the direction of travel. For example, for a turbine engine, the forward position refers to a position on the turbine engine close to the propeller or fan, and the aft position refers to a position on the turbine engine away from the propeller or fan.

[0015] As used herein, "below" means Figure 1A and Figure 1B Turbine engine 10 is shown in an orientation in which one component is located radially below the other component.

[0016] As used herein, “top” means that in the orientation of turbine engine 10 shown in the figures, a radially outward surface or radially outward end of a component is radially higher than “bottom”.

[0017] The terms “coupled,” “fixed,” “attached,” “connected,” and the like refer to both direct coupling, fixing, attachment, or connection as well as indirect coupling, fixing, attachment, or connection through one or more intermediate components or features, unless otherwise indicated herein.

[0018] The singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise.

[0019] As used herein, the terms "axial" and "axially" refer to directions and orientations extending substantially parallel to the centerline of the turbine engine. Additionally, the terms "radial" and "radially" refer to directions and orientations extending substantially perpendicular to the centerline of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations extending arcuately around the centerline of the turbine engine.

[0020] As used herein, "top" refers to the highest or uppermost point, portion or surface of a component in the orientation shown in the drawing.

[0021] As used herein, "bottom" refers to the lowest or lowermost point, portion or surface of a component in the orientation shown in the drawing.

[0022] As described above, the reverse flow turboprop engine includes a core section disposed in an engine air chamber. The engine air chamber is a space within a turbine engine in which a turbocharger engine is disposed, as further described below. Thus, the engine air chamber is a structural element of a turbine engine that is defined within a housing of the turbine engine. The air intake of the reverse flow turboprop engine directs air from the propeller into the engine air chamber. The core section may include an inlet filter that prevents large debris in the air from entering the core section, thereby preventing foreign matter from damaging the core section (FOD). However, the inlet filter may not prevent smaller debris (e.g., ice particles) from entering the core section. Ice particles (e.g., ice crystals less than 200 microns) may form at high altitudes and may be ingested into the engine during flight. Although ice particles are described herein, the present disclosure may be used to prevent any type of solid particles (e.g., ice, dust, sand, etc.) whose size is such that the inlet filter cannot prevent such solid particles from entering the core section.

[0023] Particles can be ingested with the air flow through the air inlet. These particles can rebound from the cold surfaces in the air inlet and the engine air chamber, and can flow into the engine inlet and enter the core section of the engine. When the particles are ice particles, the ice particles can accumulate and form larger ice blocks. Therefore, the particles can damage the components of the core section. The damaged components may cause the compressor to surge or stall, thereby reducing the air flow through the core section. The damaged components can also cause the burner to flame out, resulting in engine thrust loss. As the particles impact the blades, the damaged components can also damage the blades in the compressor or turbine section. In some cases, particles, especially ice particles, may cause engine power loss during flight. When the turbine engine is a turboprop engine, these problems are particularly difficult to avoid due to the geometry of the turboprop engine's air inlet and engine air chamber compared to other types of turbine engines (e.g., turbofan engines including annular inlets).

[0024] Current particle ingestion prevention devices utilize heated surfaces in the air intake to melt ice particles or utilize centrifugal force to separate particles from the air flow. However, such devices add complexity and weight to the turbine engine. In addition, the heated surfaces may unintentionally transfer heat to other components of the turbine engine or the aircraft, thereby overheating the other components and shortening the life cycle of the other components. Such heating devices may not be able to completely melt larger ice particles. Devices that utilize centrifugal force require additional moving parts to generate centrifugal force, thereby adding additional parts that require maintenance and may damage or fail. In addition, such devices placed in the air intake or engine plenum may cause excessive aerodynamic losses to the airflow entering the core section, thereby reducing the overall efficiency of the turbine engine.

[0025] Therefore, the present disclosure provides a particle deflector assembly, which includes one or more particle deflector walls positioned in an engine air chamber for deflecting particles and preventing particles from flowing into a core section. The particle deflector assembly is positioned below (e.g., radially outward and below) the engine inlet of the core section, in an area where the air flow velocity is low and the particle inertia is high, to allow particles to separate from the air flow. Specifically, the particle deflector assembly is positioned at the air chamber end wall of the engine air chamber, wherein the air chamber end wall redirects the air flow from the air inlet toward the core section. In some embodiments, the particle deflector assembly includes a metal sheet that is connected to the air chamber end wall below the core section and extends into the engine air chamber. The particles impact the metal sheet, so that the metal sheet prevents the particles from flowing through the engine inlet to the core section and prevents the particles from recirculating in the engine air chamber. In this way, the particles are blocked and collected at the bottom of the engine air chamber. The particle capture efficiency can be improved by using multiple metal sheets and segmenting the particle deflector assembly. In some embodiments, the particle deflector assembly includes one or more heated surfaces to induce melting and vaporization of the particles, thereby preventing the particles from recirculating within the engine air chamber.

[0026] Thus, the present disclosure provides an improved and simplified particle deflector assembly that prevents particles from entering the core section of a turbine engine without unduly sacrificing aerodynamic performance of the air inlet or engine plenum compared to a turbine engine without the benefit of the present disclosure.

[0027] Now referring to the accompanying drawings, Figure 1A 1 is a schematic partial cross-sectional view of a turbine engine 10 according to an embodiment of the present disclosure. The turbine engine 10 is a turboprop engine and has a longitudinal centerline axis 12. Figure 1AAs shown, the turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline axis 12 for reference), a radial direction R orthogonal to the axial direction A, and a circumferential direction C disposed about the axial direction A. Generally speaking, the turbine engine 10 includes a propeller section 14 and a turbocharger engine 16 disposed downstream of the propeller section 14. The propeller section 14 is driven by the turbocharger engine 16, as described in further detail below.

[0028] Turbine engine 10 includes an air inlet 17 located behind propeller section 14 and in front of turbocharger engine 16. Air inlet 17 is a scoop-shaped inlet located radially outward from longitudinal centerline axis 12. Figure 1A and Figure 1B In the embodiment of FIG. 1 , the air inlet 17 is positioned at the radial bottom portion of the turbine engine 10 (e.g., at Figure 1A 1 below the longitudinal centerline axis 12 in the orientation shown in FIG. 1 ). For example, an air inlet 17 is positioned below the propeller section 14. The air inlet 17 may be positioned at any radial position of the turbine engine 10 (e.g., on a side of the turbine engine 10 or on a radial top portion of the turbine engine 10). The air inlet 17 directs air from the propeller section 14 into the turbocharger engine 16, as further described below. The depicted turbocharger engine 16 generally includes an outer casing 18 that is substantially tubular and defines a radial inlet 20 at the axial rearward end of the turbocharger engine 16. The outer casing 18 encapsulates a compressor 22, a combustor 26, a turbine section 27 including a high pressure (HP) turbine 28 and a downstream low pressure (LP) turbine 30, and an exhaust section 32 in a series flow relationship. A high pressure (HP) shaft 34 or spool drives the HP turbine 28 to the compressor 22 so that the HP turbine 28 and the compressor 22 rotate in unison. A low pressure (LP) shaft 36 drivingly connects LP turbine 30 to propeller section 14 such that LP turbine 30 and propeller section 14 rotate in unison. Compressor 22, combustor 26, turbine section 27, and exhaust section 32 together define a core air flow path for turbine engine 10.

[0029] Propeller section 14 includes a propeller 38 having a plurality of propeller blades 40 ( Figure 1A4 and 5). The propeller 38 is a plurality of gears that are arranged on the upper and lower surfaces of the propeller 38. ... The disk 42 is covered by a rotatable propeller hub 48 having an aerodynamic profile to facilitate airflow through the plurality of propeller blades 40 .

[0030] Figure 1B is a schematic partial cross-sectional view of an aircraft 90 including a turbine engine 10 according to the present disclosure. Figure 1B As shown, the shroud 49 circumferentially surrounds the turbine engine 10 and provides an aerodynamic surface so that air flows over the shroud 49. The turbocharger engine 16 is disposed within the shroud 49. The turbine engine 10 includes an intake duct 50 within the shroud 49, the intake duct 50 being fluidly coupled to the air inlet 17. The intake duct 50 is a flow path that guides air passing through the propeller blades 40 into the air inlet 17 and reaches the radial inlet 20 of the turbine engine 10, as described in further detail below. The intake duct 50 is defined between an inner duct wall 52 and an outer duct wall 54. The inner duct wall 52 is located radially inward of the outer duct wall 54 from the longitudinal centerline axis 12. The intake duct 50 includes a generally axial duct portion 55 and a radially angled duct portion 56. The radially angled duct portion 56 is downstream of the generally axial duct portion 55. At the generally axial duct portion 55, the inner duct wall 52 and the outer duct wall 54 extend generally axially rearward from the air inlet 17. At the radially angled duct portion 56, the outer duct wall 54 includes a radially angled duct wall 57 that is radially angled toward the longitudinal centerline axis 12. As such, the radially angled duct portion 56 is angled toward the longitudinal centerline axis 12 such that the radially angled duct portion 56 directs air flowing through the intake duct 50 toward the radial inlet 20, as described in further detail below. Figure 1B , the radially angled duct portion 56 (eg, radially angled duct wall 57) is angled at approximately 30° relative to the longitudinal centerline axis 12. The radially angled duct portion 56 may include any angle relative to the longitudinal centerline axis 12 from 0° to 90°.

[0031] The turbine engine 10 includes an engine plenum 58 that is in fluid communication with the air intake duct 50 and is located within the shroud 49. For example, the engine plenum 58 is fluidly coupled to the radially angled duct portion 56 of the air intake duct 50. The engine plenum 58 is a structural element that is defined as a space within the turbine engine 10 for accommodating the turbocharger engine 16. The turbocharger engine 16 is disposed within the engine plenum 58. The engine plenum 58 is at least partially defined by a plenum end wall 59 that defines the rear wall of the turbine engine 10 and separates the turbine engine 10 from the rest of the aircraft 90. Air flows from the radially angled duct portion 56 into the engine plenum 58 and is directed into the radial inlet 20, as described in further detail below. The engine plenum 58 has an axial plenum length extending in the axial direction A, a radial plenum height extending in the radial direction R, and a circumferential plenum width extending in the circumferential direction C. The radially angled duct wall 57 defines a bottom surface of the engine plenum 58 and defines a circumferential plenum width of the engine plenum 58 .

[0032] refer to Figure 1A and Figure 1B During operation of turbine engine 10, a volume of air 60 passes through propeller blades 40 of propeller 38. As volume of air 60 passes through multiple propeller blades 40, a first portion of the air, referred to as bypass air 62, is directed or delivered over shroud 49 ( Figure 1B ), and a second portion of the air, referred to as core air 64, is directed or delivered through the air intake 17 into the intake duct 50. The intake duct 50 directs the core air 64 axially rearward toward the turbocharger engine 16. Specifically, the generally axial duct portion 55 directs the core air 64 axially rearward from the air intake 17. The radially angled duct portion 56 directs the core air 64 from the generally axial duct portion 55 to the engine plenum 58. For example, a portion of the core air 64 impacts the radially angled duct wall 57, causing the core air 64 to be redirected and radially angled from the generally axial duct portion 55 toward the engine plenum 58. The core air 64 impacts the plenum end wall 59 and is directed into the radial inlet 20, causing the core air 64 to enter the turbocharger engine 16. For example, the core air 64 flows generally radially into the radial inlet 20. In some examples, the average path of the core air 64 enters the engine plenum 58 in the range of 30° to 90° relative to the average path of the air entering the radial inlet 20. The radial inlet 20 includes an inlet screen 21 (eg, a foreign object debris (FOD) screen) disposed about the radial inlet 20 that prevents undesirable debris from entering the turbocharger engine 16. The turbine engine 10 also includes a particle deflector assembly 100 (eg, a particle deflector assembly 100 disposed about the radial inlet 20). Figure 1B), is used to prevent smaller particles, such as ice particles or other solid particles (such as dust, sand, etc.), from entering the turbocharger engine 16, as further described below.

[0033] The turbocharger engine 16 is a reverse flow engine such that the core air 64 flows through the turbocharger engine 16 from the rear end of the turbocharger engine 16 to the front end of the turbocharger engine 16. In this way, the turbine engine 10 is referred to as a reverse flow turboprop engine. The radial inlet 20 directs the core air 64 downstream to the compressor 22. In the compressor 22, the pressure of the core air 64 is increased to form compressed air 66 ( Figure 1A ), and the compressed air 66 is delivered to the combustor 26 where it is mixed with fuel and combusted to produce combustion gases 68 ( Figure 1A ).exist Figure 1A and Figure 1B In the embodiment of FIG. 5 , combustor 26 is a reverse flow combustor such that compressed air 66 flows from compressor 22, around combustor 26, and enters combustor 26 at a forward end of combustor 26. In this manner, compressed air 66 flows rearward within combustor 26, and then combustion gases 68 are directed forward from combustor 26 to turbine section 27.

[0034] In turbine section 27, combustion gases 68 are delivered to HP turbine 28 ( Figure 1A ) and expands through the HP turbine 28, wherein a portion of the heat and kinetic energy from the combustion gases 68 is transferred via the HP turbine stator blades coupled to the outer casing 18 and coupled to the HP shaft 34 ( Figure 1A ) of the HP turbine rotor blades, thereby causing the HP shaft 34 to rotate, thereby supporting the operation of the compressor 22. The combustion gases 68 are then delivered to the LP turbine 30 ( Figure 1A ) and expands through the LP turbine 30. Here, the second portion of the heat and kinetic energy is transferred via the LP turbine stator blades coupled to the outer casing 18 and coupled to the LP shaft 36 ( Figure 1A ) of the LP turbine rotor blades extracts from the combustion gases 68, thereby causing the LP shaft 36 to rotate, thereby rotating the LP shaft 36 via the gearbox assembly 46 ( Figure 1A ) causes the propeller 38 to rotate. The combustion gases 68 are then routed through the exhaust section 32 and out of the turbocharger engine 16 to provide propulsive thrust.

[0035] During operation, particles (e.g., ice particles, dust, sand, etc.) in the core air 64 may enter the radial inlet 20 and, thereby, enter the turbocharger engine 16. In such an event, the particles may damage components of the turbocharger engine 16 (e.g., the compressor 22, the combustor 26, or the turbine section 27) or may reduce the aerodynamic efficiency of components of the turbocharger engine 16. Accordingly, the present disclosure provides a particle deflector assembly 100 that prevents particles in the core air 64 from entering the radial inlet 20, and, therefore, the turbocharger engine 16, as described in further detail below.

[0036] Figure 1A and Figure 1B The depicted turbine engine 10 is provided as an example only. In other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. For example, in other exemplary embodiments, the propeller 38 may be configured in any other suitable manner (e.g., as a fixed pitch propeller) and may also be supported using any other suitable propeller frame configuration. Furthermore, in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In certain exemplary embodiments, Figures 1A to 1C The turbine engine 10 may be used to drive a propeller of a helicopter, may be used in aeroderivative applications, or may be attached to a propeller of an aircraft. Additionally, in other exemplary embodiments, the turbine engine 10 may include any other suitable type of combustor and may not include the depicted exemplary reverse flow combustor.

[0037] Figure 1C is according to the present disclosure along the longitudinal centerline axis 12 and Figure 1B Detail 1C of FIG. 1 is a schematic cross-sectional view of a portion of an engine plenum 58 of a turbine engine 10 including a particle deflector assembly 100. Figure 1C As shown, the core air 64 (eg, Figure 1CThe average (e.g., mean) path of the core air 64 (depicted by the arrow streamlines in FIG. 1 ) is generally parallel to the radial angled duct wall 57. The average path of the core air 64 may be at an angle of plus or minus twenty degrees (±20°) relative to the radial angled duct wall 57 due to the core air 64 being directed toward the radial inlet 20 within the engine plenum 58. The particle deflector assembly 100 causes a portion of the core air 64 to separate from the radial angled duct wall 57 and create a low momentum flow of the core air 64, also referred to as a recirculation zone 101. The portion of the core air 64 that forms the recirculation zone 101 creates a swirl or vortex of the core air 64 to define the recirculation zone 101. As such, the recirculation zone 101 includes that portion of the core air 64 that swirls or recirculates within the recirculation zone 101. The velocity of the portion of the core air 64 in the recirculation zone 101 is lower than the velocity of the core air 64 directed into the radial inlet 20 (e.g., the core air 64 located outside of the recirculation zone 101).

[0038] The particle deflector assembly 100 deflects particles in the core air 64, and the recirculation zone 101 decelerates the particles and prevents the particles from flowing toward and into the radial inlet 20, as described in further detail below. In this way, the particle deflector assembly 100 separates particles from the core air 64 and captures the particles to prevent the particles from entering the turbocharger engine 16 (e.g., through the radial inlet 20). Figure 1C In the embodiment of the present invention, the particle deflector assembly 100 deflects particles such that the particles are spread circumferentially along the particle deflector assembly 100. The particle deflector assembly 100 also captures particles within the recirculation zone 101.

[0039] The particle deflector assembly 100 is positioned radially between the radial inlet 20 and the radially angled duct wall 57. Specifically, the particle deflector assembly 100 is positioned in an area of ​​the engine air chamber 58 where the inertia of the particles is high such that the particles do not follow the average path of the core air 64. For example, the particle deflector assembly 100 is positioned in an area of ​​the engine air chamber 58 where the average path of the particles (as indicated by the dashed arrow 65) deviates from the average path of the core air 64 by at least ten degrees (10°). Specifically, the particle deflector assembly 100 is positioned radially inward of (e.g., closer to) the area where the average path of the particles deviates from the average path of the core air 64. Figure 1B In this way, the particle deflector assembly 100 captures particles that separate from the core air 64 and flow toward the plenum end wall 59. In some embodiments, the particle deflector assembly 100 is positioned in an area of ​​the engine plenum 58 where the average path of the particles deviates from the average path of the core air 64 by a range of ten to forty-five degrees (10° to 45°).

[0040] The particle deflector assembly 100 is disposed at the plenum end wall 59 in an area of ​​the engine plenum 58 where the kinetic energy of the particles is greater than the kinetic energy of the core air 64, causing the particles to continue their path toward the plenum end wall 59 while the engine plenum 58 redirects the core air 64 toward the radial inlet 20. In this way, the particle deflector assembly 100 is positioned in an area where it is difficult for particles to follow the flow of the core air 64, which is diverted toward the radial inlet 20 as the core air 64 impacts the plenum end wall 59. Such a location of the particle deflector assembly 100 provides for separating a majority (e.g., greater than 50%) of the particles from the core air 64 without unduly sacrificing the aerodynamic performance of the intake duct 50 (e.g., without unduly reducing the air pressure of the core air 64 within the intake duct 50 or introducing additional pressure losses within the intake duct 50).

[0041] The particle deflector assembly 100 includes one or more deflector end walls 102 and one or more particle deflector walls 104 that are angled with the one or more deflector end walls 102. The one or more deflector end walls 102 extend generally radially along a radial direction R and are coupled to the plenum end wall 59 such that the one or more deflector end walls 102 form a portion of the plenum end wall 59. The one or more deflector end walls 102 may be coupled to the plenum end wall 59 by any coupling means, such as bolts, welding, etc. In some embodiments, the one or more deflector end walls 102 are formed together with the plenum end wall 59 such that the one or more deflector end walls 102 and the plenum end wall 59 form a single integral component.

[0042] One or more particle deflector walls 104 extend from the one or more deflector end walls 102. The one or more particle deflector walls 104 are angled at a core air deflector angle relative to the average path of the core air 64 in the engine air chamber 58. The core air deflector angle is measured from the average path of the core air 64 to the one or more particle deflector walls 104 (e.g., to one or more particle deflector surfaces 106 of the one or more particle deflector walls 104). For example, the core air deflector angle is greater than 0° and less than or equal to 60°, so that particles in the core air 64 impact the one or more particle deflector walls 104, and the one or more particle deflector walls 104 prevent particles from entering the radial inlet 20. The one or more particle deflector walls 104 extend axially forward from the bottom end of the one or more deflector end walls 102 and extend into the engine air chamber 58. In some embodiments, the deflector angle of the one or more particle deflector walls 104 is substantially equal to the angle of the radially angled duct wall 57 relative to the air chamber end wall 59.

[0043] In some embodiments, the one or more particle deflector walls 104 are angled at a particle deflector angle relative to the average path of particles in the engine air chamber 58 (as shown by the dashed arrow 65). The particle deflector angle is measured from the average path of the particles to the one or more particle deflector walls 104 (e.g., to the one or more particle deflector surfaces 106 of the one or more particle deflector walls 104). For example, the particle deflector angle is in the range of 30° to 90° so that particles in the core air 64 impact the one or more particle deflector walls 104, and the one or more particle deflector walls 104 prevent the particles from entering the radial inlet 20.

[0044] The particle deflector assembly 100 includes one or more particle deflector surfaces 106 that deflect particles and prevent particles from flowing toward the radial inlet 20. The one or more particle deflector surfaces 106 are defined by the bottom surface of the one or more particle deflector walls 104. As such, the one or more particle deflector surfaces 106 extend axially forward of the plenum end wall 59 and into the engine plenum 58 such that particles impact the one or more particle deflector surfaces 106, as described in further detail below.

[0045] The particle deflector assembly 100 has an axial deflector length extending in the axial direction A, a radial deflector height extending in the radial direction R, and a circumferential direction C ( Figure 1B ). The axial deflector length is defined as the length measured along the axial direction A from the air chamber end wall 59 to the axial front end of the particle deflector assembly 100 (e.g., one or more particle deflector walls 104). The radial deflector height is defined as the height measured along the radial direction R from the bottom surface (e.g., one or more particle deflector surfaces 106) at the axial front end of the particle deflector assembly 100 (e.g., one or more particle deflector surfaces 106) to the top surface at the radial top end of the particle deflector assembly 100 (e.g., at the top surface of one or more deflector end walls 102). The circumferential deflector width is defined as the length measured along the circumferential direction C ( Figure 1B ) is the width measured from the circumferential front surface of the particle deflector assembly 100 to the circumferential rear surface of the particle deflector assembly 100.

[0046] exist Figure 1B and Figure 1CIn some embodiments, the circumferential deflector width of the particle deflector assembly 100 is substantially equal to the circumferential plenum width of the engine plenum 58. Thus, the particle deflector assembly 100 extends substantially the entire circumferential plenum width. In some embodiments, the circumferential deflector width is less than the circumferential plenum width such that the particle deflector assembly 100 extends only partially along the circumferential plenum width of the engine plenum 58. The axial deflector length is equal to or less than 70% of the axial length of the radial inlet 20. The radial deflector height is equal to or less than 60% of the radial height of the plenum end wall 59 from the radial angled duct wall 57 at the plenum end wall 59 to the radial inner surface of the radial inlet 20. Thus, the particle deflector assembly 100 has the advantage of preventing a majority (e.g., at least 50%) of the particles in the core air 64 from entering the turbocharger engine 16 ( Figure 1B ) (e.g., the surface area defined by the axial deflector length and the circumferential deflector width). The values ​​of the axial deflector length and the radial deflector height are exemplary only, and these values ​​may vary based on the specific engine plenum configuration.

[0047] The particle deflector assembly 100 is formed from one or more sheets of material, such as metal or the like. The particle deflector assembly 100 can be made of any material that prevents particles in the core air 64 from entering the radial inlet 20. In some embodiments, the particle deflector assembly 100 can be segmented such that the particle deflector assembly 100 is made of a plurality of segments. In some embodiments, the particle deflector assembly 100 includes an exhaust flow opening defined by one or more particle deflector walls 104 that direct a portion of the core air 64 through the exhaust flow opening and out of the particle deflector assembly 100 such that the portion of the core air 64 flows toward the turbocharger engine 16 (e.g., toward the radial inlet 20). In some embodiments, the particle deflector assembly 100 (e.g., one or more particle deflector walls 104) is heated such that the particle deflector assembly 100 melts particles that contact the particle deflector assembly 100. For example, the particle deflector assembly 100 may be heated by coils disposed within the particle deflector assembly 100 (e.g., within one or more particle deflector walls 104). In some embodiments, the heat from the compressor 22 ( Figure 1A ) is directed toward the particle deflector assembly 100 to heat the particle deflector assembly 100. Heating the particle deflector assembly 100 helps capture particles within the particle deflector assembly 100 (e.g., within the recirculation zone 101).

[0048] In operation, the core air 64 flows through the engine plenum 58, impacts the plenum end wall 59, and is directed into the radial inlet 20, as described in detail above. Particles in the core air 64 separate from the core air 64 (e.g., the average path of the particles deviates from the average path of the core air 64) and impact the plenum end wall 59 and flow in the direction of the radial inlet 20 (as shown by the dashed arrow 65). The particle deflector assembly 100 prevents the particles from continuing to flow toward the radial inlet 20 and prevents the particles from entering the radial inlet 20. Specifically, the particles impact one or more particle deflector walls 104 (e.g., one or more particle deflector surfaces 106) of the particle deflector assembly 100. In this way, the particle deflector assembly 100 captures the particles and prevents the particles from continuing to flow toward the radial inlet 20 and prevents the particles from entering the radial inlet 20, and thus prevents the particles from entering the turbocharger engine 16 ( Figure 1A and Figure 1B ).

[0049] When a particle impacts one or more particle deflector walls 104, the particle deflector assembly 100 decelerates the particle so that the particle falls toward the recirculation zone 101 and away from the radial inlet 20. Upon impacting the plenum end wall 59, a portion of the particle may be decelerated so that the portion of the particle falls toward the recirculation zone 101 without contacting the particle deflector assembly 100. The recirculation zone 101 circulates the particle so that the recirculation zone 101 prevents the particle from flowing back into the flow of the core air 64. In this way, the particle deflector assembly 100 separates the particle from the core air 64 and captures the particle to prevent the particle from entering the radial inlet 20. The particle deflector assembly 100 helps capture particles at the bottom of the engine plenum 58 (e.g., on the radially angled duct wall 57).

[0050] Figure 2A is a schematic cross-sectional view of a particle deflector assembly 200 for a turbine engine 10 taken along a longitudinal centerline axis of the particle deflector assembly 200 according to another embodiment. Figure 2B A portion of a particle deflector assembly 200 is shown isolated from a turbine engine 10 in accordance with the present disclosure. The particle deflector assembly 200 causes a portion of the core air 64 to separate from the radially angled duct wall 57 and creates a low momentum flow of the core air 64, also referred to as a recirculation zone 201. The particle deflector assembly 200 is substantially similar to Figure 1B and Figure 1CThe particle deflector assembly 200 is similar to the particle deflector assembly 100 and is positioned within the engine air chamber 58 similar to the particle deflector assembly 100. The particle deflector assembly 200 includes one or more deflector end walls 202 and one or more particle deflector walls 204. The particle deflector assembly 200 includes an axial deflector length, a radial deflector height, and a circumferential deflector width. The axial deflector length is defined as the length measured along the axial direction A from the air chamber end wall 59 to the axial front end of the particle deflector assembly 200 (e.g., one or more particle deflector walls 204). The radial deflector height is defined as the height measured along the radial direction R from the bottom surface at the axial front end of the particle deflector assembly 200 (e.g., the deflector bottom wall 220) to the top surface at the radial top end of the particle deflector assembly 200 (e.g., the top surface of one or more deflector end walls 202). The circumferential deflector width is defined as the length of the particle deflector assembly 200 along the circumferential direction C ( Figure 1B ) is the width measured from the circumferential front surface of the particle deflector assembly 200 to the circumferential rear surface of the particle deflector assembly 200.

[0051] One or more deflector end walls 202 are coupled to or formed with the air chamber end wall 59 such that the one or more deflector end walls 202 form a portion of the air chamber end wall 59. In this way, the particle deflector assembly 200 is disposed at the air chamber end wall 59. One or more particle deflector walls 204 are positioned at the top end of the particle deflector assembly 200. The one or more particle deflector walls 204 include a first particle deflector wall 204a and a second particle deflector wall 204b. The first particle deflector wall 204a is axially spaced forward from the one or more deflector end walls 202. The first particle deflector wall 204a is angled relative to the average path of the core air 64 at a core air deflector angle greater than 0° and less than or equal to 60°. In some embodiments, the first particle deflector wall 204a is angled relative to the average path of the particles (as shown by the dashed arrow 65) at a particle deflector angle greater than 10°, preferably in the range of 30° to 90°. The second particle deflector wall 204b is positioned at a top end of the one or more deflector end walls 202 and extends generally axially forwardly therefrom.

[0052] The particle deflector assembly 200 includes one or more particle deflector surfaces 206, and particles impact the particle deflector surfaces 206, so that the particle deflector assembly 200 captures particles and prevents particles from flowing toward the radial inlet 20. The one or more particle deflector surfaces 206 are defined by the bottom surface of the one or more particle deflector walls 204, so that particles impact the bottom surface of the one or more particle deflector walls 204. The one or more particle deflector surfaces 206 include a first particle deflector surface 206a and a second particle deflector surface 206b. The first particle deflector surface 206a is defined by the bottom surface of the first particle deflector wall 204a. The second particle deflector surface 206b is defined by the bottom surface of the second particle deflector wall 204b.

[0053] The particle deflector assembly 200 also includes a louver assembly 210 and a plurality of vertical segmented walls 216. The louver assembly 210 includes a first louver wall 212a and a second louver wall 212b. The first louver wall 212a is defined by the first particle deflector wall 204a at an axially rearward end thereof and extends generally toward one or more deflector end walls 202 (e.g., toward the plenum end wall 59). The second louver wall 212b is defined by the second particle deflector wall 204b at an axially forward end thereof and extends generally radially toward the radially angled duct wall 57.

[0054] The first particle deflector wall 204a is axially spaced forward from the second particle deflector wall 204b such that the first louver wall 212a is axially spaced forward from the second louver wall 212b. Thus, the particle deflector assembly 200 includes an exhaust flow opening 214 defined between the first particle deflector wall (e.g., the first louver wall 212a) and the second particle deflector wall 204b (e.g., the second louver wall 212b). Figure 2B As shown, the exhaust flow openings 214 include a single exhaust flow opening 214 that extends the entire circumferential deflector width of the particle deflector assembly 200. In some embodiments, the particle deflector assembly 200 includes a plurality of exhaust flow openings 214 spaced apart along the circumferential deflector width of the particle deflector assembly 200.

[0055] The particle deflector assembly 200 also includes a deflector bottom wall 220 that contacts the radially angled conduit wall 57 such that the deflector bottom wall 220 forms a portion of the radially angled conduit wall 57. In some embodiments, the deflector bottom wall 220 is coupled to the radially angled conduit wall 57 or forms a single integral component with the radially angled conduit wall 57. A plurality of vertical segmented walls 216 extend from the deflector bottom wall 220 to the top end of the particle deflector assembly 200. One or more deflector end walls 202 and one or more particle deflector walls 204 are coupled to the plurality of vertical segmented walls 216. The plurality of vertical segmented walls 216 are circumferentially spaced apart along the circumferential deflector width such that the particle deflector assembly 200 is segmented to define one or more deflector chambers 218. Each of the one or more deflector chambers 218 is defined between two vertical segmented walls of the plurality of vertical segmented walls 216. The one or more deflector chambers 218 retain particles captured by the particle deflector assembly 200.

[0056] Operation of the particle deflector assembly 200 Figure 1B and Figure 1C The operation of the particle deflector assembly 100 is substantially similar. Specifically, the core air 64 flows through the engine air chamber 58, impacts the air chamber end wall 59, and is directed into the radial inlet 20, as described in detail above. The particles in the core air 64 impact the air chamber end wall 59 and flow into one or more deflector chambers 218 (as shown by the dashed arrow 65). In this way, the particle deflector assembly 200 captures particles and prevents particles from entering the radial inlet 20. Specifically, the particles impact the air chamber end wall 59 (e.g., one or more deflector end walls 202) within the one or more deflector chambers 218. A portion of the particles impacts one or more particle deflector walls 204 (e.g., one or more particle deflector surfaces 206). For example, the portion of the particles can impact at least one of the first particle deflector wall 204a (e.g., the first particle deflector surface 206a) and the second particle deflector wall 204b (e.g., the second particle deflector surface 206b). In this way, the particle deflector assembly 200 prevents particles from continuing to flow toward the radial inlet 20 and entering the turbocharger engine 16 through the radial inlet 20 ( Figure 1A and Figure 1B ).

[0057] When particles impact the plenum end wall 59 (e.g., one or more deflector end walls 202) and one or more particle deflector walls 204, the particle deflector assembly 200 decelerates the particles so that the particles fall toward the recirculation zone 201 and away from the radial inlet 20. The recirculation zone 201 circulates the particles so that the recirculation zone 201 prevents the particles from flowing back into the flow of the core air 64. In this way, the particle deflector assembly 200 separates the particles from the core air 64 and captures the particles to prevent the particles from entering the radial inlet 20. The particle deflector assembly 200 helps to decelerate the particles at the bottom of the engine plenum 58 (e.g., on the radially angled duct wall 57) ( Figure 1B ) to collect particles. One or more deflector chambers 218 facilitate collection of particles than those without multiple vertical segmented walls. Figure 1B and Figure 1C The particle deflector assembly 100 can deflect a greater number of particles.

[0058] The exhaust flow opening 214 directs a portion of the core air 64 from the one or more deflector chambers 218 so that the portion of the core air 64 flows from the particle deflector assembly 200 to the radial inlet 20 ( Figure 1B ). The size of the exhaust flow opening 214 is designed to control the amount of the portion of the core air 64 that flows through the exhaust flow opening 214 and control the size of the recirculation zone 201. The size of the exhaust flow opening 214 is selected to allow the core air 64 to flow therethrough while also preventing particles from escaping the particle deflector assembly 200.

[0059] Figure 3 3 is a schematic cross-sectional view of a particle deflector assembly 300 for a turbine engine 10 taken along a longitudinal centerline axis of the particle deflector assembly 300 according to another embodiment. The particle deflector assembly 300 causes a portion of the core air 64 to separate from the radially angled duct wall 57 and creates a low momentum flow of the core air 64, also referred to as a recirculation zone 301. The recirculation zone 301 is defined by one or more deflector chambers 318, as described in further detail below. The particle deflector assembly 300 is substantially similar to Figures 1B to 1C and Figures 2A to 2B The particle deflector assembly 300 is similar to the particle deflector assembly 100, 200 and is positioned in the engine air chamber 58 similar to the particle deflector assembly 100, 200. The particle deflector assembly 300 includes an axial deflector length, a radial deflector height, and a circumferential deflector width. The particle deflector assembly 300 includes one or more deflector end walls 302, one or more particle deflector walls 304, a plurality of vertical segmented walls 316, one or more deflector chambers 318, and a deflector bottom wall 320.

[0060] One or more deflector end walls 302 are coupled to or formed with the air chamber end wall 59 such that the one or more deflector end walls 302 form a portion of the air chamber end wall 59. In this way, the particle deflector assembly 300 is disposed at the air chamber end wall 59. The one or more particle deflector walls 304 include a first particle deflector wall 304a and a second particle deflector wall 304b. The first particle deflector wall 304a is positioned at the front end of the particle deflector assembly 300 and extends in the radial direction R and is angled axially rearward toward the one or more deflector end walls 302. The first particle deflector wall 304a is angled relative to the average path of the core air 64 at a core air deflector angle greater than 0° and less than or equal to 60°. In some embodiments, the first particle deflector wall 304a is angled relative to the average path of the particles (as shown by the dashed arrow 65) at a particle deflector angle in the range of 30° to 90°.

[0061] The second particle deflector wall 304b is positioned at the top end of the particle deflector assembly 300 (e.g., closer to the radially outward end of the radial inlet 20) and is axially spaced forward from the air chamber end wall 59. Thus, the particle deflector assembly 300 includes an exhaust flow opening 314 defined between the air chamber end wall 59 and the second particle deflector wall 304b. The second particle deflector wall 304b is a curved wall that deflects particles into one or more deflector chambers 318. For example, the second particle deflector wall 304b is a generally U-shaped wall that prevents particles from flowing toward the radial inlet 20 and directs particles into the particle deflector assembly 300 (e.g., into one or more deflector chambers 318). The second particle deflector wall 304b is radially spaced from the first particle deflector wall 304a so that the chamber opening 330 is defined between the first particle deflector wall 304a and the second particle deflector wall 304b.

[0062] The particle deflector assembly 300 includes a plurality of particle deflector surfaces 306, including a first particle deflector surface 306a and a second particle deflector surface 306b. The first particle deflector surface 306a is defined by the top surface of the first particle deflector wall 304a, and the second particle deflector surface 306b is defined by the bottom surface of the second particle deflector wall 304b. In this way, particles impact the first particle deflector surface 306a of the first particle deflector wall 304a and the second particle deflector surface 306b of the second particle deflector wall 304b, so that the particle deflector assembly 300 guides the particles into one or more particle deflector chambers 318 to capture the particles, as further described below.

[0063] A plurality of vertical segmented walls 316 extend from the deflector bottom wall 320 to the top of the particle deflector assembly 300. One or more deflector end walls 302 and one or more particle deflector walls 304 are coupled to the plurality of vertical segmented walls 316. The plurality of vertical segmented walls 316 are circumferentially spaced apart along the circumferential deflector width so that the particle deflector assembly 300 is segmented into a plurality of particle deflector segments. Thus, the particle deflector assembly 300 includes one or more deflector chambers 318. Each of the one or more deflector chambers 318 is defined between two vertical segmented walls of the plurality of vertical segmented walls 316. The one or more deflector chambers 318 retain particles collected by the particle deflector assembly 300.

[0064] The particle deflector assembly 300 includes one or more deflector chamber walls 340 disposed within the one or more deflector chambers 318. The one or more deflector chamber walls are radially spaced below the second particle deflector wall 304b and extend generally axially forward from the one or more deflector end walls 302, for example. The one or more deflector end walls 302 extend radially from the deflector bottom wall 320 to the one or more deflector chamber walls 340. Thus, the one or more deflector end walls 302 extend only a portion of the radial height of the particle deflector assembly 300, and the one or more deflector chamber walls 340 are positioned at the top end of the one or more deflector end walls 302. In some embodiments, the one or more deflector chamber walls 340 extend the entire or substantially the entire radial deflector height of the particle deflector assembly 300, and the one or more deflector chamber walls 340 are radially positioned between the deflector bottom wall 320 and the second particle deflector wall 304b. Each of the one or more deflector chambers 318 defines a recirculation zone 301 such that the recirculation zone 301 is defined between a deflector bottom wall 320, one or more deflector chamber walls 340, one or more deflector end walls 302, and a first particle deflector wall 304a.

[0065] Operation of the particle deflector assembly 300 Figures 1B to 1C and Figures 2A to 2B The operation of the particle deflector assembly 100, 200 is substantially similar. Specifically, the core air 64 flows through the engine air chamber 58, impacts the air chamber end wall 59, and is directed into the radial inlet 20, as described in detail above. The particle deflector assembly 300 prevents particles from entering the radial inlet 20. The particles in the core air 64 flow toward the particle deflector assembly 300 (as shown by the dashed arrow 65) and impact one or more particle deflector walls 304 (e.g., impact one or more particle deflector surfaces 306). Specifically, the particles impact the first particle deflector wall 304a (e.g., the first particle deflector surface 306a), and the first particle deflector wall 304a guides the particles radially and axially toward the second particle deflector wall 304b (e.g., the second particle deflector surface 306b).

[0066] The particles impact the second particle deflector wall 304b (e.g., the second particle deflector surface 306b) and the second particle deflector wall 304b directs the particles into the one or more deflector chambers 318. The second particle deflector wall 304b is shaped to direct the particles between the first particle deflector wall 304a and the one or more deflector chamber walls 340 within the one or more deflector chambers 318. In this way, the particle deflector assembly 300 directs the particles under the one or more deflector chamber walls 340 such that the one or more deflector chamber walls 340 prevent the particles from flowing from the particle deflector assembly 300 toward the radial inlet 20. In this way, the particle deflector assembly 300 captures the particles therein.

[0067] A portion of the core air 64 also flows into the particle deflector assembly 300 and into one or more deflector chambers 318. The exhaust flow openings 314 direct a portion of the core air 64 from the one or more deflector chambers 318 so that the portion of the core air 64 flows from the particle deflector assembly 300 to the radial inlet 20 ( Figure 1B ).

[0068] Thus, the present disclosure provides an improved and simplified particle deflector assembly that prevents particles from entering a turbocharger engine without changing the structure of the air intake, air intake duct, or engine plenum. The particle deflector assembly of the present disclosure prevents particles from entering a turbocharger engine without unduly sacrificing the aerodynamic performance of the air intake or engine plenum as compared to a turbine engine without the benefit of the present disclosure. The recirculation zone decelerates particles such that the particle deflector assembly prevents particles from flowing into the turbocharger engine through a radial inlet.

[0069] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0070] A turbine engine comprises: an engine air chamber, which is arranged in the turbine engine and is at least partially defined by an air chamber end wall; a turbocharger engine, which is arranged in the engine air chamber, and the turbine engine causes core air to flow through the engine air chamber and enter the turbocharger engine; and a particle deflector assembly, which is arranged at the air chamber end wall, and the particle deflector assembly includes one or more particle deflector walls, which extend into the engine air chamber and capture particles in the core air.

[0071] A turbine engine as described in the preceding clause, wherein said one or more particle deflector walls extend away from said plenum end wall and into said engine plenum.

[0072] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly prevents the particles from entering the turbocharger engine.

[0073] According to a turbine engine described in any of the preceding items, the one or more particle deflector walls of the particle deflector assembly define a recirculation zone, so that the one or more particle deflector walls cause a portion of the core air to produce a swirling flow of the portion of the core air within the recirculation zone, and the recirculation zone decelerates the particles.

[0074] According to a turbine engine described in any of the preceding items, the one or more particle deflector walls include one or more particle deflector surfaces, at least one of the one or more particle deflector surfaces is defined by the bottom surface of the one or more particle deflector walls, and the particles impact the one or more particle deflector surfaces.

[0075] A turbine engine according to any preceding clause, wherein the particle deflector assembly defines an exhaust flow opening defined by the one or more particle deflector walls, the exhaust flow opening directing a portion of the core air entering the exhaust flow opening to flow out of the particle deflector assembly and toward the turbocharger engine.

[0076] A turbine engine according to any preceding clause, wherein the particle deflector assembly is positioned radially inwardly and axially rearwardly of a region of the engine plenum in which the mean path of the particles deviates from the mean path of the core air by a range of 10° to 45°.

[0077] According to a turbine engine as described in any of the preceding items, the one or more particle deflector walls include at least one particle deflector wall, and the at least one particle deflector wall is arranged at a particle deflector angle relative to the average path of the particles, and the particle deflector angle is in the range of 30° to 90°.

[0078] A turbine engine as claimed in any preceding clause, the turbocharger engine defining a radial inlet for receiving the core air into the turbocharger engine, and the particle deflector assembly being positioned upstream of the radial inlet.

[0079] A turbine engine as claimed in any preceding clause, wherein the mean path of the core air entering the engine plenum is angled in the range 30° to 90° relative to the mean path of the core air entering the radial inlet.

[0080] A turbine engine according to any preceding clause, further comprising a propeller drivingly coupled to the turbocharger engine, the propeller rotating to direct the core air into the engine plenum.

[0081] A turbine engine according to any preceding clause, further comprising a longitudinal centerline axis and an air inlet in fluid communication with the engine plenum and located radially outward from the longitudinal centerline axis, the air inlet directing the core air from the propeller to the engine plenum.

[0082] A turbine engine according to any preceding clause, further comprising an intake duct defined between the air intake and the engine plenum, the intake duct providing fluid communication between the air intake and the engine plenum and directing the core air from the air intake to the engine plenum.

[0083] A turbine engine as claimed in any preceding clause, being a turboprop engine.

[0084] A turbine engine as claimed in any preceding clause, the turbocharger engine comprising a compressor, a combustor and a turbine section.

[0085] A turbine engine as claimed in any preceding clause, wherein the compressor is axially rearward of the combustor and the combustor is axially rearward of the turbine section.

[0086] A turbine engine as claimed in any preceding clause, wherein the turbocharger engine is axially rearward of the propeller.

[0087] A turbine engine as claimed in any preceding clause, wherein the core air flows into a compressor and the compressor compresses the core air to produce compressed air.

[0088] A turbine engine as claimed in any preceding clause, wherein the compressed air flows into the combustor and mixes with fuel to produce a fuel-air mixture, and the combustor combusts the fuel-air mixture to produce combustion gases.

[0089] A turbine engine as claimed in any preceding clause, wherein the combustion gases flow from the combustor to the turbine section.

[0090] A turbine engine as claimed in any preceding clause, wherein the turbine section expands the combustion gases and directs the combustion gases out of the turbine engine through an exhaust section.

[0091] A turbine engine as claimed in any preceding clause, wherein the turbine section comprises a low pressure turbine and a high pressure turbine.

[0092] A turbine engine as claimed in any preceding clause, the compressor being drivingly coupled to the high pressure turbine such that rotation of the high pressure turbine rotates the compressor.

[0093] A turbine engine as claimed in any preceding clause, wherein the propeller is drivingly coupled to the low pressure turbine such that rotation of the low pressure turbine rotates the propeller.

[0094] A turbine engine according to any preceding clause, further comprising a gearbox assembly, said propeller being drivingly coupled to said low pressure turbine via said gearbox assembly.

[0095] A turbine engine according to any preceding clause, further comprising a low pressure shaft to which said propeller and said low pressure turbine are drivingly coupled.

[0096] A turbine engine according to any preceding clause, further comprising a high pressure shaft to which said compressor and said high pressure turbine are drivingly coupled.

[0097] A turbine engine as claimed in any preceding clause, the turbine engine being a reverse flow engine such that the core air flows through the turbocharger engine from a rearward end of the turbocharger engine to a forward end of the turbocharger engine.

[0098] A turbine engine according to any preceding clause, further comprising an air intake duct defined between an air intake and said engine plenum, said air intake duct directing said core air from said air intake to said engine plenum.

[0099] A turbine engine as claimed in any preceding clause, wherein the inlet duct is defined by an inner duct wall and an outer duct wall.

[0100] A turbine engine as claimed in any preceding clause, wherein the air inlet duct comprises a radially angled duct portion angled towards the engine plenum, the radially angled duct portion changing the angle of the core air towards the engine plenum.

[0101] A turbine engine as claimed in any preceding clause, wherein the angled duct portion comprises a radially angled duct wall defining a bottom surface of the engine plenum.

[0102] A turbine engine as claimed in any preceding clause, the turbine engine having an axial direction, a radial direction and a circumferential direction.

[0103] A turbine engine according to any preceding clause, wherein the engine air chamber has an axial air chamber length extending in the axial direction, a radial air chamber height extending in the radial direction, and a circumferential air chamber width extending in the circumferential direction.

[0104] A turbine engine as claimed in any preceding clause, wherein the radial inlet comprises an inlet screen, the inlet screen preventing foreign matter debris from entering the turbocharger engine.

[0105] A turbine engine as in any preceding clause, said particle deflector assembly separating a portion of said core air from said radially angled duct wall to produce said recirculation zone.

[0106] A turbine engine as claimed in any preceding clause, wherein the velocity of the portion of the core air in the recirculation zone is less than the velocity of the core air entering the turbocharger engine.

[0107] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly is positioned between the turbocharger engine and the radially angled duct wall.

[0108] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly is positioned in a region of the engine plenum in which the mean path of the particles deviates by at least 10° from the mean path of the core air.

[0109] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly is positioned upstream of the turbocharger engine.

[0110] A turbine engine as claimed in any preceding clause, wherein said mean path of said core air is angled at ±20° relative to said radially angled duct wall.

[0111] A turbine engine as claimed in any preceding clause, wherein the one or more particle deflector walls deflect the particles such that the particles are spread circumferentially along the particle deflector assembly.

[0112] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly prevents at least 50% of the particles entering the air intake from entering the turbocharger engine.

[0113] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly comprises one or more deflector end walls disposed at the plenum end wall and extending generally radially.

[0114] A turbine engine as claimed in any preceding clause, wherein said one or more particle deflector walls extend from said one or more deflector end walls.

[0115] A turbine engine as claimed in any preceding clause, wherein said one or more particle deflector walls direct said particles towards said recirculation zone when said particles impact said one or more particle deflector walls.

[0116] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly has a circumferential deflector width extending in the circumferential direction.

[0117] A turbine engine according to any preceding clause, wherein said circumferential deflector width is substantially equal to said circumferential plenum width of said engine plenum.

[0118] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly is formed from one or more metal sheets.

[0119] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly is heated such that the particle deflector assembly melts the particles contacting the particle deflector assembly.

[0120] A turbine engine as claimed in any preceding clause, wherein the one or more particle deflector walls are positioned at a top end of the particle deflector assembly.

[0121] A turbine engine as claimed in any preceding clause, wherein the one or more particle deflector walls comprise a first particle deflector wall and a second particle deflector wall.

[0122] A turbine engine as claimed in any preceding clause, wherein the first particle deflector wall is axially forwardly spaced from the second particle deflector wall.

[0123] A turbine engine as claimed in any preceding clause, wherein the first particle deflector wall is angled at the deflector angle.

[0124] A turbine engine as claimed in any preceding clause, wherein the second particle deflector wall is positioned at a top end of the one or more deflector end walls and extends generally axially forwardly therefrom.

[0125] A turbine engine as claimed in any preceding clause, the one or more particle deflector surfaces comprising a first particle deflector surface defined by a bottom surface of the first particle deflector wall.

[0126] A turbine engine as claimed in any preceding clause, the one or more particle deflector surfaces comprising a second particle deflector surface defined by a bottom surface of the second particle deflector wall.

[0127] A turbine engine as claimed in any preceding clause, wherein the first particle deflector wall is axially spaced from the second particle deflector wall to define the exhaust flow opening.

[0128] A turbine engine as in any preceding clause, the particle deflector assembly further comprising a louver assembly including a first louver wall and a second louver wall axially spaced from the first louver wall to define the exhaust flow opening.

[0129] A turbine engine as claimed in any preceding clause, wherein the first louver wall is defined by the first particle deflector wall.

[0130] A turbine engine as claimed in any preceding clause, wherein the second louver wall is defined by the second particle deflector wall.

[0131] A turbine engine as claimed in any preceding clause, the particle deflector assembly comprising a deflector bottom wall contacting the radially angled duct wall.

[0132] A turbine engine as described in any preceding clause, further comprising a plurality of vertical segmented walls extending from said deflector bottom wall to said top end of said particle deflector assembly.

[0133] A turbine engine as claimed in any preceding clause, wherein said plurality of vertical segmented walls are circumferentially spaced apart along said circumferential deflector width of said particle deflector assembly.

[0134] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly defines one or more deflector chambers between the plurality of vertical segmented walls.

[0135] A turbine engine according to any preceding clause, wherein said one or more deflector chambers retain said particles therein.

[0136] A turbine engine as claimed in any preceding clause, wherein the first particle deflector wall is located at a forward end of the particle deflector assembly and extends in the radial direction.

[0137] A turbine engine as claimed in any preceding clause, wherein the first particle deflector wall is angled axially rearwardly towards the one or more deflector end walls.

[0138] A turbine engine as claimed in any preceding clause, the second particle deflector wall being positioned at a top end of the particle deflector assembly and spaced axially forwardly from the plenum end wall.

[0139] A turbine engine as claimed in any preceding clause, said exhaust flow opening being defined between said plenum end wall and said second particle deflector wall.

[0140] A turbine engine as claimed in any preceding clause, wherein the second particle deflector wall is a curved wall that directs the particles into the one or more deflector chambers.

[0141] A turbine engine as claimed in any preceding clause, the second particle deflector wall being radially spaced from the first particle deflector wall such that a chamber opening is defined between the first particle deflector wall and the second particle deflector wall.

[0142] A turbine engine as claimed in any preceding clause, wherein the first particle deflector surface is defined by a top surface of the first particle deflector wall such that the particles impact the first particle deflector surface and the first particle deflector wall directs the particles towards the second particle deflector wall.

[0143] According to a turbine engine described in any of the preceding items, the second particle deflector surface is defined by the bottom surface of the second particle deflector wall, so that the particles from the first particle deflector wall impact the second particle deflector surface and the second particle deflector wall guides the particles into the one or more deflector chambers.

[0144] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly comprises one or more deflector chamber walls disposed within and extending axially within the one or more deflector chambers.

[0145] A turbine engine as claimed in any preceding clause, wherein said one or more deflector chamber walls extend generally axially forwardly from said one or more deflector end walls.

[0146] A turbine engine as claimed in any preceding clause, wherein the one or more deflector chamber walls are radially spaced from the second particle deflector wall and axially spaced rearwardly from the first particle deflector wall within the one or more deflector chambers.

[0147] According to a turbine engine described in any of the preceding items, the one or more particle deflector walls include at least one particle deflector wall, and the at least one particle deflector wall is arranged at a core air deflector angle relative to the average path of the core air in the engine air chamber, and the core air deflector angle is in the range of 0° to 60°.

[0148] A turbine engine as claimed in any preceding clause, said particle deflector assembly being positioned at the intersection of said mean path of said core air entering said engine plenum and said mean path of said air entering said radial inlet.

[0149] A turbine engine as claimed in any preceding clause, wherein the radial inlet is arranged at an axially rearward end of the turbocharger engine.

[0150] An engine air chamber for a turbine engine, comprising: an air chamber end wall at least partially defining the engine air chamber; a turbocharger engine disposed within the engine air chamber, the turbine engine causing core air to flow through the engine air chamber and into the turbocharger engine; and a particle deflector assembly disposed at the air chamber end wall, the particle deflector assembly comprising one or more particle deflector walls extending into the engine air chamber and capturing particles within the core air.

[0151] An engine plenum as described in the preceding clause, wherein the one or more particle deflector walls extend away from the plenum end wall and into the engine plenum.

[0152] An engine plenum as claimed in any preceding clause, wherein said particle deflector assembly prevents said particles from entering said turbocharger engine.

[0153] According to the engine air chamber described in any of the preceding items, the one or more particle deflector walls of the particle deflector assembly define a recirculation zone, so that the one or more particle deflector walls cause a portion of the core air to produce a swirling flow of the portion of the core air within the recirculation zone, and the recirculation zone decelerates the particles.

[0154] According to any of the preceding clauses, the one or more particle deflector walls include one or more particle deflector surfaces, at least one of the one or more particle deflector surfaces is defined by a bottom surface of the one or more particle deflector walls, and the particles impact the one or more particle deflector surfaces.

[0155] An engine plenum as described in any preceding clause, the particle deflector assembly defining an exhaust flow opening defined by the one or more particle deflector walls, the exhaust flow opening directing a portion of the core air entering the exhaust flow opening to flow out of the particle deflector assembly and toward the turbocharger engine.

[0156] An engine plenum as claimed in any preceding clause, wherein the particle deflector assembly is positioned radially inwardly and axially rearwardly of a region of the engine plenum in which the mean path of the particles deviates from the mean path of the core air by a range of 10° to 45°.

[0157] According to the engine air chamber described in any of the preceding items, the one or more particle deflector walls include at least one particle deflector wall, and the at least one particle deflector wall is arranged at a particle deflector angle relative to the average path of the particles, and the particle deflector angle is in the range of 30° to 90°.

[0158] An engine plenum as claimed in any preceding clause, the turbocharger engine defining a radial inlet for receiving the core air into the turbocharger engine, and the particle deflector assembly being positioned upstream of the radial inlet.

[0159] An engine plenum as claimed in any preceding clause, wherein the mean path of the core air entering the engine plenum is angled in the range of 30° to 90° relative to the mean path of the core air entering the radial inlet.

[0160] An engine plenum as claimed in any preceding clause, wherein the turbine engine is a turboprop engine.

[0161] An engine plenum as claimed in any preceding clause, the turbocharger engine comprising a compressor, a combustor and a turbine section.

[0162] An engine plenum as claimed in any preceding clause, wherein the compressor is axially rearward of the combustor and the combustor is axially rearward of the turbine section.

[0163] An engine plenum as claimed in any preceding clause, wherein the turbocharger engine is axially rearward of the propeller.

[0164] An engine air chamber as claimed in any preceding clause, wherein the core air flows into the compressor and the compressor compresses the core air to produce compressed air.

[0165] An engine plenum as claimed in any preceding clause, wherein the compressed air flows into the combustor and mixes with fuel to produce a fuel-air mixture, and the combustor combusts the fuel-air mixture to produce combustion gases.

[0166] An engine plenum as defined in any preceding clause, wherein the combustion gases flow from the combustor to the turbine section.

[0167] An engine plenum as claimed in any preceding clause, wherein the turbine section expands the combustion gases and directs the combustion gases out of the turbine engine through an exhaust section.

[0168] An engine chamber as described in any preceding clause, wherein the turbine section comprises a low pressure turbine and a high pressure turbine.

[0169] An engine plenum as claimed in any preceding clause, the compressor being drivingly coupled to the high pressure turbine such that rotation of the high pressure turbine causes rotation of the compressor.

[0170] An engine plenum as claimed in any preceding clause, wherein the turbine engine is a reverse flow engine such that the core air flows through the turbocharger engine from a rearward end of the turbocharger engine to a forward end of the turbocharger engine.

[0171] An engine air chamber as described in any preceding clause, the engine air chamber having an axial direction, a radial direction and a circumferential direction.

[0172] An engine air chamber according to any preceding clause, the engine air chamber having an axial air chamber length extending in the axial direction, a radial air chamber height extending in the radial direction and a circumferential air chamber width extending in the circumferential direction.

[0173] An engine plenum as claimed in any preceding clause, wherein said radial inlet comprises an inlet screen, said inlet screen preventing foreign matter debris from entering said turbocharger engine.

[0174] An engine plenum as in any preceding clause, said particle deflector assembly separating a portion of said core air from said radially angled duct wall to create said recirculation zone.

[0175] An engine plenum as claimed in any preceding clause, wherein the velocity of the portion of the core air in the recirculation zone is less than the velocity of the core air entering the turbine engine.

[0176] An engine plenum as claimed in any preceding clause, said particle deflector assembly being positioned between said turbocharger engine and said radially angled duct wall.

[0177] An engine plenum as claimed in any preceding clause, the particle deflector assembly being positioned in a region of the engine plenum where the mean path of the particles deviates by at least 10° from the mean path of the core air.

[0178] An engine plenum as claimed in any preceding clause, said particle deflector assembly being positioned upstream of said turbocharger engine.

[0179] An engine plenum as claimed in any preceding clause, wherein said mean path of said core air is at an angle of ±20° relative to said radially angled duct wall.

[0180] An engine plenum as claimed in any preceding clause, wherein said one or more particle deflector walls deflect said particles such that said particles are spread circumferentially along said particle deflector assembly.

[0181] An engine plenum as claimed in any preceding clause, wherein said particle deflector assembly prevents at least 50% of said particles entering said air intake from entering said turbocharger engine.

[0182] An engine plenum as claimed in any preceding clause, the particle deflector assembly comprising one or more deflector end walls disposed at the plenum end wall and extending generally radially.

[0183] An engine plenum as claimed in any preceding clause, wherein said one or more particle deflector walls extend from said one or more deflector end walls.

[0184] An engine plenum as claimed in any preceding clause, wherein said one or more particle deflector walls direct said particles towards said recirculation zone when said particles impact said one or more particle deflector walls.

[0185] An engine plenum as claimed in any preceding clause, said particle deflector assembly having a circumferential deflector width extending in said circumferential direction.

[0186] An engine plenum as claimed in any preceding clause, wherein said circumferential deflector width is substantially equal to said circumferential plenum width of said engine plenum.

[0187] An engine plenum as claimed in any preceding clause, wherein the particle deflector assembly is formed from one or more metal sheets.

[0188] An engine plenum as claimed in any preceding clause, wherein the particle deflector assembly is heated such that the particle deflector assembly melts the particles contacting the particle deflector assembly.

[0189] An engine plenum as in any preceding clause, wherein the one or more particle deflector walls are positioned at a top end of the particle deflector assembly.

[0190] An engine plenum as in any preceding clause, wherein the one or more particle deflector walls comprise a first particle deflector wall and a second particle deflector wall.

[0191] An engine plenum as in any preceding clause, the first particle deflector wall being axially forwardly spaced from the second particle deflector wall.

[0192] An engine plenum as claimed in any preceding clause, said first particle deflector wall being angled at said deflector angle.

[0193] An engine plenum as claimed in any preceding clause, wherein the second particle deflector wall is positioned at a top end of the one or more deflector end walls and extends generally axially forwardly therefrom.

[0194] An engine plenum as claimed in any preceding clause, the one or more particle deflector surfaces comprising a first particle deflector surface defined by a bottom surface of the first particle deflector wall.

[0195] An engine plenum as claimed in any preceding clause, the one or more particle deflector surfaces comprising a second particle deflector surface defined by a bottom surface of a second particle deflector wall.

[0196] An engine plenum as in any preceding clause, the first particle deflector wall being axially spaced from the second particle deflector wall to define the exhaust flow opening.

[0197] The engine plenum of any preceding clause, the particle deflector assembly further comprising a louver assembly including a first louver wall and a second louver wall axially spaced from the first louver wall to define the exhaust flow opening.

[0198] An engine plenum as claimed in any preceding clause, wherein the first louver wall is defined by the first particle deflector wall.

[0199] An engine plenum as claimed in any preceding clause, the second louver wall being defined by the second particle deflector wall.

[0200] An engine plenum as claimed in any preceding clause, said particle deflector assembly comprising a deflector bottom wall contacting said radially angled duct wall.

[0201] An engine plenum as claimed in any preceding clause, further comprising a plurality of vertical segmented walls extending from said deflector bottom wall to said top end of said particle deflector assembly.

[0202] An engine plenum as in any preceding clause, said plurality of vertical segmented walls being circumferentially spaced along said circumferential deflector width of said particle deflector assembly.

[0203] An engine plenum as claimed in any preceding clause, wherein said particle deflector assembly defines one or more deflector chambers between said plurality of vertical segmented walls.

[0204] An engine plenum as claimed in any preceding clause, wherein said one or more deflector chambers retain said particles therein.

[0205] An engine plenum as claimed in any preceding clause, wherein the first particle deflector wall is positioned at a forward end of the particle deflector assembly and extends in the radial direction.

[0206] An engine plenum as claimed in any preceding clause, wherein the first particle deflector wall is angled axially rearwardly towards the one or more deflector end walls.

[0207] An engine plenum as claimed in any preceding clause, the second particle deflector wall being positioned at a top end of the particle deflector assembly and spaced axially forwardly from the plenum end wall.

[0208] An engine plenum as claimed in any preceding clause, said exhaust flow opening being defined between said plenum end wall and said second particle deflector wall.

[0209] An engine plenum as claimed in any preceding clause, wherein the second particle deflector wall is a curved wall that directs the particles into the one or more deflector chambers.

[0210] An engine plenum as claimed in any preceding clause, the second particle deflector wall being radially spaced from the first particle deflector wall such that a chamber opening is defined between the first particle deflector wall and the second particle deflector wall.

[0211] An engine plenum as claimed in any preceding clause, the first particle deflector surface being defined by a top surface of the first particle deflector wall such that the particles impact the first particle deflector surface and the first particle deflector wall directs the particles towards the second particle deflector wall.

[0212] An engine air chamber according to any of the preceding clauses, wherein the second particle deflector surface is defined by a bottom surface of the second particle deflector wall such that particles from the first particle deflector wall impact the second particle deflector surface and the second particle deflector wall guides the particles into the one or more deflector chambers.

[0213] A turbine engine as claimed in any preceding clause, wherein the particle deflector assembly comprises one or more deflector chamber walls disposed within and extending axially within the one or more deflector chambers.

[0214] An engine plenum as claimed in any preceding clause, wherein said one or more deflector chamber walls extend generally axially forwardly from said one or more deflector end walls.

[0215] An engine plenum as in any preceding clause, said one or more deflector chamber walls being radially spaced from said second particle deflector wall and axially spaced rearwardly from said first particle deflector wall within said one or more deflector chambers.

[0216] According to the engine air chamber described in any of the preceding items, the one or more particle deflector walls include at least one particle deflector wall, and the at least one particle deflector wall is arranged at a core air deflector angle relative to the average path of the core air in the engine air chamber, and the core air deflector angle is in the range of 0° to 60°.

[0217] An engine plenum as claimed in any preceding clause, said particle deflector assembly being positioned at the intersection of said mean path of said core air entering said engine plenum and said mean path of said air entering said radial inlet.

[0218] An engine plenum as claimed in any preceding clause, wherein the radial inlet is arranged at an axial rearward end of the turbocharger engine.

[0219] A method for separating particles in a turbine engine, the method comprising: directing core air into an engine air chamber disposed within the turbine engine and at least partially defined by an air chamber end wall, such that the core air impacts the air chamber end wall and is directed into a turbocharger engine disposed within the engine air chamber; and separating the particles within the core air using one or more particle deflector walls of a particle deflector assembly, the particle deflector assembly being disposed at the air chamber end wall and extending into the engine air chamber, such that the particle deflector assembly captures the particles.

[0220] A method according to the preceding clause, wherein the turbine engine is a turbine engine as described in any preceding clause.

[0221] A method as in any preceding clause, further comprising preventing said particles from entering said turbocharger engine using said particle deflector assembly.

[0222] A method as in any preceding clause, further comprising generating a swirling flow of a portion of the core air using the one or more particle deflector walls of the particle deflector assembly to define a recirculation zone, and decelerating the particles in the recirculation zone.

[0223] According to the method of any of the preceding items, the one or more particle deflector walls include one or more particle deflector surfaces, at least one of the one or more particle deflector surfaces is defined by the bottom surface of the one or more particle deflector walls, and the method further includes causing the particles to impact the one or more particle deflector surfaces.

[0224] A method according to any preceding clause, the particle deflector assembly further comprising an exhaust flow opening defined by the one or more particle deflector walls, and the method further comprising directing a portion of the core air out of the particle deflector assembly and towards the turbocharger engine through the exhaust flow opening.

[0225] The method according to any of the preceding clauses further includes setting at least one of the one or more particle deflector walls at a core air deflector angle relative to the air chamber end wall, so that the at least one particle deflector wall extends away from the air chamber end wall, and the core air deflector angle is in the range of 0° to 60°, and includes capturing the particles using the at least one particle deflector wall set at the core air deflector angle.

[0226] The method according to any of the preceding clauses further includes positioning the particle deflector assembly radially inwardly and axially rearwardly of an area of ​​the engine air chamber where the average path of the particles deviates from the average path of the core air by a range of 10° to 45°, and includes separating the particles from the core air at the area of ​​the engine air chamber where the average path of the particles deviates from the average path of the core air such that the particle deflector assembly captures the particles.

[0227] A method as in any preceding clause, the turbocharger engine defining a radial inlet and the particle deflector assembly being positioned upstream of the radial inlet, and the method further comprising directing the core air into the turbocharger engine through the radial inlet.

[0228] A method as in any preceding clause, the turbocharger engine comprising a propeller drivingly coupled to the turbocharger engine, and the method further comprising rotating the propeller to generate the core air and directing the core air into the engine plenum.

[0229] A method according to any of the preceding clauses, wherein the turbine engine comprises a longitudinal centerline axis and an air inlet, wherein the air inlet is fluidly connected to the engine air chamber and is positioned radially outward from the longitudinal centerline axis, and the method further comprises directing the core air from the propeller to the engine air chamber through the air inlet.

[0230] A method as claimed in any preceding clause, wherein the turbine engine is a turbine engine as claimed in any preceding clause.

[0231] A method as in any preceding clause, further comprising directing the core air into the compressor and compressing the core air with the compressor to produce compressed air.

[0232] A method as in any preceding clause, further comprising directing the compressed air into the combustor and mixing the compressed air with fuel to produce a fuel-air mixture, and combusting the fuel-air mixture with the combustor to produce combustion gases.

[0233] A method as in any preceding clause, further comprising directing the combustion gases from the combustor to the turbine section.

[0234] A method as in any preceding clause, further comprising expanding the combustion gases in the turbine section and directing the combustion gases out of the turbine engine through an exhaust section.

[0235] A method as described in any preceding clause, wherein the turbine section comprises a low pressure turbine and a high pressure turbine.

[0236] A method as claimed in any preceding clause, the compressor being drivingly coupled to the high pressure turbine and comprising rotating the compressor by rotation of the high pressure turbine.

[0237] A method as claimed in any preceding clause, the propeller being drivingly coupled to the low pressure turbine and comprising rotating the propeller by rotation of the low pressure turbine.

[0238] A method as claimed in any preceding clause, wherein the turbine engine is a reverse flow engine and the method further comprises directing the core air from a rearward end of the turbocharger engine through the turbocharger engine to a forward end of the turbocharger engine.

[0239] A method as claimed in any preceding clause, further comprising defining an intake duct between an air intake and the engine plenum, and further comprising directing the core air from the air intake to the engine plenum through the intake duct.

[0240] A method as in any preceding clause, wherein the radial inlet comprises an inlet screen, the method further comprising preventing foreign matter debris from entering the turbocharger engine using the inlet screen.

[0241] A method as claimed in any preceding clause, wherein the radial inlet is provided at an axially rearward end of the turbocharger engine.

[0242] A method as in any preceding clause, further comprising separating a portion of said core air from said radially angled duct wall to create said recirculation zone with said particle deflector assembly.

[0243] A method as in any preceding clause, further comprising causing a velocity of the portion of the core air in the recirculation zone to be less than a velocity of the core air entering the turbocharger engine.

[0244] A method as in any preceding clause, the particle deflector assembly being positioned in a region of the engine air chamber where the mean path of the particles deviates by at least 10° from the mean path of the core air.

[0245] A method as claimed in any preceding clause, wherein the particle deflector assembly is positioned in a region of the engine air chamber where the mean path of the particles deviates from the mean path of the core air by a range of 10° to 45°.

[0246] A method as in any preceding clause, wherein the mean path of the core air is at an angle of ±20° relative to the radially angled duct wall.

[0247] A method as in any preceding clause, further comprising deflecting the particles using the one or more particle deflector walls such that the particles are spread circumferentially along the particle deflector assembly.

[0248] A method as in any preceding clause, further comprising preventing at least 50% of the particles entering the air intake from entering the turbocharger engine using the particle deflector assembly.

[0249] A method as in any preceding clause, further comprising directing the particles towards the recirculation zone when the particles impact the one or more particle deflector walls.

[0250] A method according to any preceding clause, further comprising heating the particle deflector assembly such that the particles melt upon contacting the particle deflector assembly.

[0251] A method as in any preceding clause, further comprising retaining the particles within the one or more deflector chambers.

[0252] A method according to any preceding clause, further comprising directing the particles into the one or more deflector chambers through the chamber opening defined between the first particle deflector wall and the second particle deflector wall.

[0253] A method as in any preceding clause, further comprising directing the particles to impact the first particle deflector surface and directing the particles towards the second particle deflector wall using the first particle deflector wall.

[0254] The method according to any of the preceding clauses further includes directing the particles from the first particle deflector wall to the second particle deflector wall so that the particles impact the second particle deflector surface, and includes utilizing the second particle deflector wall to direct the particles into the one or more deflector chambers.

[0255] According to the method described in any of the preceding clauses, the particle deflector assembly includes one or more deflector chamber walls disposed within the one or more deflector chambers and extending axially within the one or more deflector chambers, and the method includes utilizing the one or more deflector chamber walls to prevent the particles from flowing out of the one or more deflector chambers.

[0256] According to the method described in any of the preceding clauses, the one or more particle deflector walls include at least one particle deflector wall, and the at least one particle deflector wall is arranged at a core air deflector angle relative to the average path of the core air in the engine air chamber, and the core air deflector angle is in the range of 0° to 60°.

[0257] A method as in any preceding clause, the particle deflector assembly being positioned at an intersection of the mean path of the core air entering the engine plenum and the mean path of the air entering the radial inlet.

[0258] A method as claimed in any preceding clause, wherein the mean path of the core air entering the engine plenum is at an angle in the range of 30° to 90° relative to the mean path of the air entering the radial inlet.

[0259] Although the foregoing description is directed to preferred embodiments of the present disclosure, other variations and modifications will be apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, the features described in conjunction with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A turbine engine, characterized in that: include: an engine plenum disposed within the turbine engine and at least partially defined by a plenum end wall; a turbocharger engine disposed in the engine air chamber, wherein the turbine engine causes core air to flow through the engine air chamber and into the turbocharger engine; and A particle deflector assembly is disposed at the air chamber end wall, the particle deflector assembly including one or more particle deflector walls extending into the engine air chamber and capturing particles within the core air.

2. The turbine engine according to claim 1, characterized in that The one or more particle deflector walls of the particle deflector assembly define a recirculation zone such that the one or more particle deflector walls cause a portion of the core air to generate a swirling flow of the portion of the core air within the recirculation zone, and the recirculation zone decelerates the particles.

3. The turbine engine according to claim 1, characterized in that: Wherein the one or more particle deflector walls comprise one or more particle deflector surfaces, at least one of the one or more particle deflector surfaces being defined by a bottom surface of the one or more particle deflector walls, and the particles impact the one or more particle deflector surfaces.

4. The turbine engine according to claim 1, characterized in that: Wherein the particle deflector assembly defines an exhaust flow opening defined by the one or more particle deflector walls, the exhaust flow opening directing a portion of the core air entering the exhaust flow opening to flow out of the particle deflector assembly and toward the turbocharger engine.

5. The turbine engine according to claim 1, characterized in that: The particle deflector assembly is positioned radially inwardly and axially rearwardly of a region of the engine plenum where an average path of the particles deviates from an average path of the core air by a range of 10° to 45°.

6. The turbine engine according to claim 1, characterized in that The one or more particle deflector walls include at least one particle deflector wall disposed at a particle deflector angle relative to an average path of the particles, the particle deflector angle being in the range of 30° to 90°.

7. The turbine engine according to claim 1, characterized in that Wherein the turbocharger engine defines a radial inlet for receiving the core air into the turbocharger engine, and the particle deflector assembly is positioned upstream of the radial inlet.

8. The turbine engine according to claim 7, characterized in that Wherein an average path of the core air entering the engine air chamber is at an angle in the range of 30° to 90° relative to an average path of the core air entering the radial inlet.

9. The turbine engine according to claim 1, characterized in that Further included is a propeller drivingly coupled to the turbocharger engine, the propeller rotating to direct the core air into the engine plenum.

10. The turbine engine according to claim 9, characterized in that Further including a longitudinal centerline axis and an air inlet in fluid communication with the engine plenum and located radially outward from the longitudinal centerline axis, the air inlet directing the core air from the propeller to the engine plenum.

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