Multi-stage inlet particle separator for rotary engines

Abstract

A particle separator system for a turbine engine having an engine inlet. The particle separator system includes an inlet particle separator located within the engine inlet and configured to remove particles from the incoming airflow. The particle separator system also includes a barrier filter located within the turbine engine casing, downstream of the inlet particle separator, and configured to intercept particles not removed by the inlet particle separator.

Description

Technical Field

[0001] The present disclosure relates generally to particulate separators and, in particular, to multi-stage inlet particulate separators, hybrid inlet particulate separators and barrier filters for rotary engines, and methods of separating particulates from an airflow. Background Art

[0002] An engine, particularly a gas or combustion turbine engine, is a rotary engine that extracts energy from a stream of combustion gases passing through the engine onto a plurality of turbine blades. Turbine engines have been used for land and marine sports as well as for power generation. Turbine engines are commonly used in aviation applications, such as for aircraft, including helicopters and airplanes. In aircraft, turbine engines are used to propel the aircraft. In terrestrial applications, turbine engines are commonly used for power generation. In addition, fluid systems that flow dirty fluids (e.g., fluids containing particulate matter) may include downstream engines, such as in tanks or power plants.

[0003] Turbine engines for aircraft are designed to operate at high temperatures to maximize engine efficiency, so cooling of certain engine components, such as the high-pressure turbine and the low-pressure turbine, may be required. Typically, cooling is achieved by directing or routing cooler air from the high-pressure compressor and / or the low-pressure compressor to the engine components that require cooling. Although turbine air is at a relatively high temperature, it is cooler than the compressor air and can be used to cool the turbine engine. Cooling air can be supplied to various turbine engine components, including turbine engine blades and the interior of the turbine engine shroud.

[0004] Particles in the engine intake air, such as dirt, dust, sand, volcanic ash, and other environmental pollutants, can cause severe compressor erosion. As the particles move through the turbine engine, they can melt in the combustion gases and subsequently re-solidify on the turbine flow path surfaces. Particles entrained in the turbine cooling air can cause cooling losses due to deposition and clogging of cooling passages. All of these effects reduce the operating time or "time-on-wing" (TOW) in the aircraft environment. This problem is exacerbated in certain operating environments around the world, such as deserts where turbine engines are exposed to large amounts of airborne particles. BRIEF DESCRIPTION OF THE DRAWINGS

[0005] The foregoing and other features and advantages will be apparent from the following more particular description of various exemplary embodiments, as illustrated in the drawings, in which like reference numerals generally indicate identical, functionally similar, and / or structurally similar elements.

[0006] Figure 1 is a schematic diagram of a turbine engine for an aircraft according to an embodiment of the present disclosure.

[0007] Figure 2 is a cross-sectional view of an inlet section and a duct section of a turbine engine according to an embodiment of the present disclosure, illustrating the location of a first stage inlet particle separator and the location of a second stage inlet particle separator.

[0008] Figure 3 is a cross-sectional view of an inlet section and a duct section showing the location of a first stage inlet particle separator and the location of a second stage inlet particle separator according to an embodiment of the present disclosure.

[0009] Figure 4 is a cross-sectional view of an inlet section and a duct section according to another embodiment of the present disclosure, illustrating the location of a first stage inlet particle separator and the location of a second stage inlet particle separator. DETAILED DESCRIPTION

[0010] By considering the following detailed description, drawings and claims, additional features, advantages and embodiments of the present disclosure are set forth or apparent. In addition, it should be understood that the foregoing summary and the following detailed description of the present disclosure are exemplary and are 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] A multi-stage inlet particle separator (IPS) is provided for the effective separation of contaminant particles. The multi-stage IPS includes an axial inlet particle separator (IPS) and a radial inlet particle separator. The multi-stage IPS provides a compact solution to maximize separation efficiency while reducing the space occupied by the multi-stage IPS. The combination and placement of the multi-stage inlet particle separator (IPS) provides the ability to clean the flow stream, which maximizes the amount of particulate matter removed from the turbine engine inlet to protect downstream turbine engine components, thereby increasing product life and reducing maintenance. The multi-stage IPS uses a combination of strategically placed inertial-based particle separators to remove particulate matter from the flow upstream of the turbine engine. The multi-stage IPS uses a combination of different styles of inertial particle separators, and the unique placement and / or integration of the system provides high separation efficiency, reduced space and reduced weight compared to traditional systems.

[0013] Other aspects of the present disclosure further provide a hybrid approach for a turbine engine inlet protection system. The hybrid approach couples a multi-stage IPS with another separation device (e.g., a barrier filter) to maximize separation efficiency while still providing the option of bypassing the filter when needed. In an embodiment, the barrier filter can be placed in any desired enclosure or structure downstream of the inlet particle separator. For example, the barrier filter can be located at the aircraft inlet, engine inlet, or inside the nacelle and can be placed downstream of the IPS. With this placement of the filter, the IPS can provide partially clean air to the filter, thereby reducing the load on the filter. The benefits are high levels of sand separation, ram recovery, weight reduction, and the ability to provide inlet protection from particulate matter (e.g., sand) even when the filter is bypassed. In an alternative embodiment, the hybrid approach can include an IPS (single-stage IPS or multi-stage IPS) installed upstream of another IPS (aircraft-mounted IPS or engine-mounted IPS, such as the GE CT7 engine) to achieve near-barrier filter efficiency without the need for maintenance.

[0014] This hybrid arrangement can also allow filters to be bypassed while still retaining some engine protection that barrier filter solutions currently cannot provide. Compared to existing inertial separation systems, this hybrid arrangement is a step change in particle separation. In addition, this arrangement will provide significant mission adaptability when the rotorcraft is not flying in an environment rich in particulate matter, such as a sandy environment. Therefore, this maximizes engine output and provides the end user with maximum flexibility.

[0015] Rotorcraft operating in dusty environments experience reduced engine TOW and, in some extreme cases, engine flameouts that can lead to failures or even accidents. Ingestion of fine particulate matter (e.g., sand or dust) can cause severe damage to the engine hot section, which can directly result in loss of engine power and can cause engine flameout, both of which contribute to reduced TOW. Ingestion of large sand particles can also cause severe damage to the compressor, particularly the first few rotor stages, resulting in power loss and potentially reduced operability. This can lead to engine flameout and reduced TOW.

[0016] Embodiments of the present disclosure extend the performance of a typical inlet particle separator beyond that of an inlet barrier filter only solution, while still allowing all the benefits of an inlet particle separator solution. The benefits are a high level of separation efficiency, plunger recovery, reduced weight, and the ability to provide inlet protection (sand, foreign object damage (FOD), etc.) even when the filter is bypassed. Embodiments of the present disclosure also allow for mission adaptability, which is especially important for remote missions. A high level of separation efficiency, plunger recovery, reduced weight, and the ability to provide inlet protection (sand, FOD, etc.) even when the filter is bypassed. This configuration may also allow for mission adaptability, which is especially desirable for remote missions.

[0017] Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the accompanying drawings. Like or similar designations in the drawings and the description have been used to refer to like or similar parts of the present disclosure. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of the various components. The terms "upstream" and "downstream" refer to relative directions relative to the flow of a fluid in a fluid path. For example, "upstream" refers to the direction from which a fluid is flowing and "downstream" refers to the direction toward which a fluid is flowing.

[0018] The described embodiments of the present disclosure relate to systems, methods, and other apparatus related to particle removal, particularly in turboshaft turbine engines, and more specifically, to removing particles from the engine intake airflow of a turbine engine. For illustrative purposes, the embodiments will be described with respect to aircraft turbine engines. However, it should be understood that the present disclosure is not so limited and may have general applicability in non-aircraft applications, such as other mobile applications and non-mobile industrial, commercial, and residential applications.

[0019] As used herein, the terms "radial" or "radially" refer to a dimension extending between the central longitudinal axis of an engine, the periphery of an engine, or circular or annular components disposed within an engine. The use of the terms "proximal" or "proximal," whether used alone or in combination with the terms "radial" or "radially," refers to movement in a direction toward the central longitudinal axis, or a component being relatively closer to the central longitudinal axis than another component. However, the term radial dimension should not be limited to circular or symmetrical dimensions, and may be any irregular shape (symmetrical or asymmetrical), such as an elliptical shape.

[0020] As used herein, the terms "tangential" or "tangentially" refer to a dimension extending perpendicular to a radial line relative to the longitudinal axis of the engine or a component disposed therein.

[0021] All directional references (e.g., radial, axial, up, down, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise) are for identification purposes only to assist the reader in understanding the present disclosure and do not create limitations, particularly with respect to their position, orientation, or use. Unless otherwise indicated, connection references (e.g., attach, couple, connect, and join) are to be interpreted broadly and may include intermediate members between a collection of elements and relative movement between elements. Therefore, a connection reference does not necessarily mean that two elements are directly connected and have a fixed relationship to each other. The exemplary figures are for illustrative purposes only, and the dimensions, positions, orders, and relative sizes reflected in the accompanying figures may vary.

[0022] Figure 1 1 is a schematic diagram of a turbine engine 10 for an aircraft according to an embodiment of the present disclosure. The turbine engine 10 has a generally longitudinally extending axis or engine centerline 12 extending from a front portion 14 to an aft portion 16. The turbine engine 10 includes, in downstream serial flow relationship, a compressor section 22; a combustion section 28 including a combustor 30; and a turbine section 32. The compressor section 22, the combustor 30, and the turbine section 32 form an engine core 44 of the turbine engine 10, which generates combustion gases. A casing 46 surrounds the engine core 44. All rotating parts of the turbine engine 10 are referred to individually or collectively as a rotor 51.

[0023] The compressor section 22 includes a plurality of compressor stages 52, 54 in which a set of compressor blades 56, 58 rotate relative to a set of corresponding static compressor vanes 60, 62 (also known as nozzles) to compress or pressurize the fluid flow through the stage. In a single compressor stage 52, 54, the plurality of rotating compressor blades 56, 58 may be arranged in a ring and may extend radially outward from the blade platform to the blade tip relative to the engine centerline 12, while the corresponding static compressor vanes 60, 62 are positioned downstream of and adjacent to the rotating compressor blades 56, 58. It should be noted that Figure 1 The number of blades, vanes, and compressor stages shown in FIG are selected for illustrative purposes only, and other numbers are possible. Rotating compressor blades 56, 58 for one stage of the compressor may be mounted to disk 53 as part of rotor 51, with each stage having its own disk. Static compressor vanes 60, 62 are mounted to casing 46 in a circumferential arrangement around rotor 51.

[0024] The turbine section 32 includes a plurality of turbine stages 64, 66 in which a set of turbine blades 68, 70 rotate relative to a set of corresponding static turbine buckets 72, 74 (also known as nozzles) to extract energy from the fluid flow passing through the stage. In a single turbine stage 64, 66, the plurality of rotating turbine blades 68, 70 may be arranged in a ring and may extend radially outward from the blade platform to the blade tip relative to the engine centerline 12, while the corresponding static turbine buckets 72, 74 are positioned upstream of and adjacent to the rotating turbine blades 68, 70. Note that Figure 1 The number of blades, buckets, and turbine stages shown in FIG. 5 is chosen for illustrative purposes only; other numbers are possible.

[0025] In operation, air is supplied to compressor section 22 where ambient air is pressurized. The pressurized air is mixed with fuel and ignited in combustor 30 to generate combustion gases. Turbine section 32 extracts work from these gases, which drives compressor section 22.

[0026] Some of the ambient air may bypass the engine core 44 and be used to cool portions of the turbine engine 10, particularly the hot portion, and / or to cool or power other aspects of the aircraft. In the case of a turbine engine, the hot portion of the turbine engine 10 is typically downstream of the combustor 30, particularly the turbine section 32, as it is directly downstream of the combustion section 28. Another source of cooling fluid may be, but is not limited to, fluid exhausted from the compressor section 22.

[0027] Turbine engine 10 also includes a duct section 82 having a flow duct 106 that fluidly couples compressor section 22 to inlet section 80 of turbine engine 10. Inlet section 80 is located axially forward of compressor section 22. Inlet 90 provides access to inlet duct 96 that is fluidly coupled to flow duct 106. Air flow provided to inlet 90 can flow around center body 92, through inlet duct 96, and into flow duct 106, thereby providing air to compressor section 22. Turbine engine 10 also includes an outlet section 84 that is axially downstream of engine core 44 and has one or more struts 105 radially arranged about engine centerline 12.

[0028] Inlet section 80 further includes an inlet 90 and an inlet particle separator 88 within a center body 92. Inlet 90 defines an opening for providing air flow to the downstream section. Axially downstream of inlet 90 is center body 92 having an impact surface 94 formed by a portion of center body 92 opposite the air flow provided through the opening of inlet 90. An inlet duct 96 is defined by the shape of center body 92, as will be described in further detail below.

[0029] The inlet particle separator 88 includes a first-stage inlet particle separator 98 and a second-stage inlet particle separator 100. The first-stage inlet particle separator 98 is an axial inlet particle separator, and the second-stage inlet particle separator 100 is a radial inlet particle separator. The first-stage inlet particle separator 98 is disposed near the inner center body 92A of the center body 92. The second-stage inlet particle separator 100 is disposed at the outer center body 92B of the center body 92. The inner center body 92A includes a plurality of first-stage scavenging vanes 92C configured to direct a portion of the air flow containing particulate matter toward the first-stage inlet particle separator 98. The first-stage inlet particle separator 98 includes an air duct 98A that bypasses the flow duct 106. The air duct 98A has an outlet 98B located outside the housing 46. The outer center body 92B includes a plurality of first-stage scavenging vanes 92C configured to direct a portion of the air flow containing particulate matter toward the second-stage inlet particle separator 100. Second stage inlet particle separator 100 includes a scavenge duct 100A that directs airflow laden with particulate matter toward second stage inlet particle separator 100. Outer center body 92B includes a plurality of second stage scavenge vanes 92D configured to direct airflow toward second stage inlet particle separator 100.

[0030] Outer center body 92B is radially spaced apart from inner center body 92A. Outer housing 46 is radially spaced apart from outer center body 92B. Inner center body 92A and outer center body 92B define a first inlet conduit 110 between inner center body 92A and outer center body 92B. Outer center body 92B and outer housing 46 define a second inlet conduit 112 between outer center body 92B and outer housing 46. Second inlet conduit 112 is in fluid communication with flow conduit 106 and inlet conduit 96.

[0031] The inlet 90 and outer center body 92B are annular, while the inner center body 92A is tapered such that the inlet duct 96 , the first inlet duct 110 , and the second inlet duct 112 are radially defined about the engine centerline 12 .

[0032] Figure 2 FIG is a cross-sectional view of the inlet section 80 and the duct section 82 according to an embodiment of the present disclosure, showing the location of the first stage inlet particle separator 98 and the location of the second stage inlet particle separator 100. Figure 2 As shown, the first stage inlet particle separator 98 is disposed near the inner center body 92A of the center body 92. The second stage inlet particle separator 100 is disposed at the outer center body 92B of the center body 92. The second stage inlet particle separator 100 includes a scavenging air duct 100A that directs the airflow carrying particulate matter to the second stage inlet particle separator 100. Figure 2As shown, an airflow containing particulate matter, indicated by three arrows 200, 202, and 204, is drawn through the inlet 90. The airflow contains various particles. The particles can generally be divided into two types of particles, a first type of particle containing primarily momentum-dominated particles and a second type of particle containing primarily drag-dominated particles. Momentum-dominated particles are generally relatively large particles, while drag-dominated particles are generally relatively small particles. The airflow containing momentum-dominated particles, depicted by arrows 200, tends to be directed toward the engine centerline 12 (e.g., through the first inlet duct 110). Figure 1 ). An airflow containing drag-dominant particles, depicted by arrows 204, tends to be drawn in radially outward of inlet 90 through second inlet duct 112. Some momentum-dominant particles in airflow 200 (the first airflow) and drag-dominant particles in airflow 204 (the second airflow) impact impact surface 94, formed by a portion of outer centerbody 92B of centerbody 92. The shape and configuration of impact surface 94 isolate the momentum-dominant particles from the drag-dominant particles. For example, the shape, positioning, and / or orientation of impact surface 94 can be selected to achieve a desired separation or isolation of the momentum-dominant particles from the drag-dominant particles. Upon impacting impact surface 94, the momentum-dominant particles in airflow 200 will tend to be directed toward inner centerbody 92A and through first inlet duct 110 to be collected by first-stage inlet particle separator 98. Upon impacting impact surface 94, the drag-dominant particles in airflow 204 will tend to be directed toward outer centerbody 92B and through second inlet duct 112 to be collected by second-stage inlet particle separator 100. The relatively clean airflow (third airflow) depicted by arrow 202 is substantially unaffected by the shape or configuration of the impact surface 94 because it carries no particulate matter and continues to flow through the flow conduit 106. A blower system (not shown) may be provided at the outlet of the first-stage inlet particle separator 98 and the outlet of the second-stage inlet particle separator 100 to draw the airflow 200 containing momentum-dominant particles and / or the airflow 204 containing drag-dominant particles. The blower system may be two separate blowers for each of the airflow 200 and the airflow 204, or a common blower for both the airflow 200 and the airflow 204. As can be appreciated, the impact surface 94 is configured to separate the airflow containing momentum-dominant particles and drag-dominant particles into a first airflow 200 containing substantially momentum-dominant particles and a second airflow 204 containing substantially drag-dominant particles, and direct the first airflow 200 toward the first-stage inlet particle separator 98 and the second airflow 204 toward the second-stage inlet particle separator 100.

[0033] Figure 3 The inlet section 80 and the conduit section 82 (eg, Figure 1), showing the position of the first stage inlet particle separator 98 and the position of the second stage inlet particle separator 100. Figure 3 A first stage inlet particle separator 98 is depicted disposed adjacent the inner center body 92A of the center body 92. A second stage inlet particle separator 100 is disposed at the outer center body 92B of the center body 92. The inner center body 92A includes a plurality of first stage scavenging vanes 92C configured to direct a portion of the air flow containing particulate matter toward the first stage inlet particle separator 98. The plurality of first stage scavenging vanes 92C are configured to rotate counterclockwise when facing the inlet 90 to direct the air flow laden with momentum-dominant particles toward the blower system 400 (e.g., Figure 1 As shown). The second stage inlet particle separator 100 includes a purge air duct 100A, which guides the air flow with particulate matter to the second stage inlet particle separator 100 and then to the blower system 400. Figure 3 As shown, the scavenging air duct 100A is circumferentially wound around the outer casing 46, which surrounds the engine core 44 (e.g., Figure 1 shown).

[0034] Figure 4 The inlet section 80 and the conduit section 82 (eg, Figure 1 ), showing the position of the first stage inlet particle separator 98 and the position of the second stage inlet particle separator 100. Figure 4 An inner center body 92A is shown including a plurality of first stage scavenging vanes 92C configured to direct a portion of the air flow containing particulate matter toward a first stage inlet particle separator 98. The first stage inlet particle separator 98 includes an air duct 98A having an outlet 98B located outside the housing 46. Additionally, in this embodiment, as shown in FIG. Figure 4As shown, a barrier filter 300 is disposed within the flow duct 106 that fluidly couples the compressor section 22 to the engine inlet 90 in the inlet section 80 of the turbine engine 10. The barrier filter 300 intercepts particles in the airflow 202 that may not have been removed using the first-stage inlet particle separator 98 or the second-stage inlet particle separator 100. The barrier filter 300 can be placed downstream of the first-stage inlet particle separator 98 and the second-stage inlet particle separator 100. With this placement of the barrier filter 300, the first-stage inlet particle separator 98, along with the second-stage inlet particle separator 100, can provide partially cleaned air to the barrier filter 300, thereby reducing the load on the barrier filter 300. Some benefits of this configuration include high levels of particle separation, plunger recovery, and weight reduction, as well as the ability to provide inlet protection from particulate matter even when the barrier filter 300 is bypassed. Therefore, in some applications, the barrier filter 300 may not be required, and particle reduction or elimination can be achieved solely by using the first-stage inlet particle separator 98 coupled with the second-stage inlet particle separator 100. However, in other applications, such as when a turbine engine (e.g., on an aircraft) is operated in an environment rich in particulate matter, the barrier filter 300 can be used to provide an additional filtration system to remove particulate matter that may have escaped the filtration system using the first stage inlet particle separator 98 and the second stage inlet particle separator 100. The barrier filter 300 can be made of a porous material or porous filter media that allows fluid to pass but substantially blocks or filters out solid particles. For example, the barrier filter 300 can be formed of a porous media that separates suspended solid matter particles from the airflow by allowing airflow to pass through the pores of the porous media while intercepting and blocking the solid matter particles because the solid matter particles are larger than the size of the pores of the porous media.

[0035] This can provide significant mission flexibility for a rotorcraft equipped with a turbine engine that has the option of including or bypassing the barrier filter 300 when not operating in an environment rich in particulate matter (e.g., a sandy environment), thereby maximizing engine output, thereby providing maximum flexibility to the end user.

[0036] Thus, the configuration described herein allows for mission adaptability that may be required for remote missions, particularly high levels of separation efficiency, plunger recovery and weight reduction, as well as the ability to provide inlet protection (sand, FOD, etc.) even when the filter is bypassed.

[0037] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0038] A particle separator system for a turbine engine having an engine inlet in an inlet section. The particle separator system includes an inlet particle separator located within the engine inlet and configured to remove particles from an incoming airflow. The particle separator system further includes a barrier filter located within a casing of the turbine engine, downstream of the inlet particle separator, the barrier filter configured to intercept particles not removed by the inlet particle separator.

[0039] The inlet particle separator of any preceding clause, comprising: a first-stage inlet particle separator disposed adjacent an inner centerbody of the engine inlet; and a second-stage inlet particle separator disposed adjacent an outer centerbody of the engine inlet, the outer centerbody having an impact surface facing an incoming airflow through the engine inlet, the impact surface being configured to separate an airflow containing momentum-dominant particles and drag-dominant particles into a first airflow containing substantially momentum-dominant particles and a second airflow containing substantially drag-dominant particles, and directing the first airflow toward the first-stage inlet particle separator and directing the second airflow toward the second-stage inlet particle separator.

[0040] The particle separator system of any preceding clause, wherein the inner centerbody includes first stage scavenging vanes configured to direct the first airflow having the momentum leading particles toward the first stage inlet particle separator.

[0041] The particle separator system of any preceding clause, wherein the outer centerbody includes second stage scavenging vanes configured to direct the second airflow toward the second stage inlet particle separator.

[0042] The particle separator system of any preceding clause, wherein the first stage inlet particle separator comprises a duct that bypasses a flow duct configured to direct airflow to a compressor section of the turbine engine.

[0043] A particle separator system according to any preceding clause, wherein the duct has an outlet located external to the casing of the turbine engine.

[0044] A particle separator system as in any preceding clause, wherein the first stage inlet particle separator has a first conduit and the second stage inlet particle separator has a second conduit.

[0045] A turbine engine includes an engine inlet having an inlet particle separator positioned and configured to remove particles from an incoming airflow. The turbine engine also includes a barrier filter positioned within a casing of the turbine engine, downstream of the inlet particle separator, the barrier filter configured to intercept particles not removed by the inlet particle separator.

[0046] An engine inlet includes an inner centerbody, an outer centerbody radially spaced from the inner centerbody, and an outer shell radially spaced from the outer centerbody, the inner and outer centerbody defining a first inlet duct therebetween, and the outer centerbody and outer shell defining a second inlet duct therebetween. The engine inlet further includes a first-stage inlet particle separator disposed adjacent the inner centerbody, and a second-stage inlet particle separator disposed adjacent the outer centerbody, the outer centerbody having an impact surface facing the engine inlet. The impact surface is configured to separate an airflow containing momentum-dominant particles and drag-dominant particles into a first airflow containing substantially momentum-dominant particles and a second airflow containing drag-dominant particles, directing the first airflow toward the first-stage inlet particle separator through the first inlet duct and directing the second airflow toward the second-stage inlet particle separator through the second inlet duct.

[0047] A turbine engine according to any preceding clause, further comprising an engine core disposed downstream of said inner and outer center bodies.

[0048] The turbine engine of any preceding clause, further comprising a compressor section and a flow conduit fluidly coupling the compressor section to the engine inlet.

[0049] A turbine engine as in any preceding clause, wherein said inner centerbody includes first stage scavenging vanes configured to direct said first airflow having said momentum leading particles toward said first stage inlet particle separator.

[0050] A turbine engine as in any preceding clause, wherein the outer centerbody includes second stage scavenging vanes configured to direct the second airflow toward the second stage inlet particle separator.

[0051] The turbine engine of any preceding clause, wherein the first stage inlet particle separator comprises a duct that bypasses a flow duct configured to direct airflow to a compressor section of the turbine engine.

[0052] A turbine engine according to any preceding clause, wherein the duct has an outlet located externally of the casing.

[0053] A turbine engine as in any preceding clause, wherein the first stage inlet particle separator has a first conduit and the second stage inlet particle separator has a second conduit different from the first conduit.

[0054] The turbine engine of any preceding clause, further comprising a barrier filter configured to intercept particles not cleared by the first stage inlet particle separator and the second stage inlet particle separator.

[0055] A method for separating particles from an airflow in an engine inlet, the engine inlet having an inner centerbody, an outer centerbody radially spaced from the inner centerbody, and an outer shell radially spaced from the outer centerbody, the inner and outer centerbody defining a first inlet duct between the inner and outer centerbodies, and the outer centerbody and the shell defining a second inlet duct between the outer and outer centerbodies, a first-stage inlet particle separator disposed adjacent the inner centerbody, a second-stage inlet particle separator disposed adjacent the outer centerbody, the outer centerbody having an impact surface facing the engine inlet. The method comprises: (a) receiving an airflow containing momentum-dominant particles and drag-dominant particles through the engine inlet; (b) separating the airflow containing the momentum-dominant particles and the drag-dominant particles into a first airflow containing substantially momentum-dominant particles and a second airflow containing drag-dominant particles; (c) directing the first airflow through the first inlet duct toward the first-stage inlet particle separator; and (d) directing the second airflow through the second inlet duct toward the second-stage inlet particle separator.

[0056] The method of any preceding clause, further comprising directing a third gas flow comprising a substantially reduced particulate load to a compressor section disposed downstream of the inner center body and the outer center body.

[0057] The method of any preceding clause, wherein directing the first airflow toward the first stage inlet particle separator through the first inlet duct comprises directing the first airflow having the momentum-dominant particles toward the first stage inlet particle separator using a first stage scavenging vane disposed within the inner centerbody.

[0058] The method of any preceding clause, wherein directing the second airflow toward the second stage inlet particle separator through the second inlet duct comprises directing the second airflow having drag-dominant particles toward the second stage inlet particle separator using second stage scavenging vanes disposed within the outer centerbody.

[0059] A method as in any preceding clause, further comprising directing the first airflow through a first conduit, and directing the second airflow through a second conduit different from the first conduit.

[0060] A method according to any preceding clause, wherein separating the airflow containing the momentum-dominant particles and the drag-dominant particles into a first airflow having substantially momentum-dominant particles and a second airflow having drag-dominant particles comprises separating the airflow into the first airflow, the second airflow, and a third airflow having a significantly reduced particle load.

[0061] The method of any preceding clause, further comprising intercepting particles not removed by the first stage inlet particle separator and the second stage inlet particle separator using a barrier filter.

[0062] Although the foregoing description is directed to preferred embodiments of the present disclosure, it should be noted that 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, 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 particle separator system for a turbine engine having an engine inlet, characterized in that The particle separator system comprises: an inlet particle separator located within the engine inlet and configured to remove particles from the incoming airflow, wherein the inlet particle separator comprises: a first stage inlet particle separator disposed adjacent an inner centerbody of the engine inlet; and a second stage inlet particle separator disposed adjacent an outer centerbody of the engine inlet, the outer centerbody having an impact surface facing the incoming airflow through the engine inlet, wherein the impact surface is configured to separate an airflow containing momentum-dominant particles and drag-dominant particles into a first airflow containing substantially momentum-dominant particles and a second airflow containing substantially drag-dominant particles, and to direct the first airflow toward the first stage inlet particle separator and the second airflow toward the second stage inlet particle separator; and a barrier filter located within a casing of the turbine engine and downstream of the inlet particle separator, the barrier filter being configured to intercept particles not removed by the inlet particle separator; The first stage inlet particle separator includes a duct that bypasses a flow duct configured to direct airflow to a compressor section of the turbine engine.

2. The particle separator system according to claim 1, characterized in that in, The inner centerbody includes a plurality of first stage scavenging vanes configured to direct the first airflow having the momentum-leading particles toward the first stage inlet particle separator.

3. The particle separator system according to claim 1, characterized in that in, The outer centerbody includes a plurality of second stage scavenge vanes configured to direct the second air flow toward the second stage inlet particle separator.

4. The particle separator system according to claim 1, characterized in that in, The duct has an outlet located outside the casing of the turbine engine.

5. A turbine engine, characterized in that: include: An engine inlet having an inlet particle separator positioned and configured to remove particles from an incoming airflow, wherein the engine inlet comprises: an inner center body, an outer center body radially spaced from the inner center body, and an outer shell radially spaced from the outer center body, (i) the inner center body and the outer center body defining a first inlet duct between the inner center body and the outer center body, and (ii) the outer center body and the outer shell defining a second inlet duct between the outer center body and the outer shell; a first stage inlet particle separator disposed adjacent the inner center body; and a second-stage inlet particle separator disposed adjacent the outer center body, the outer center body having an impact surface facing the engine inlet, wherein the impact surface is configured to separate an airflow containing momentum-dominant particles and drag-dominant particles into a first airflow containing substantially momentum-dominant particles and a second airflow containing drag-dominant particles, and directing the first airflow toward the first-stage inlet particle separator through the first inlet duct and directing the second airflow toward the second-stage inlet particle separator through the second inlet duct; and a barrier filter located within a casing of the turbine engine and downstream of the inlet particle separator, the barrier filter being configured to intercept particles not removed by the inlet particle separator; The first stage inlet particle separator includes a duct that bypasses a flow duct configured to direct airflow to a compressor section of the turbine engine.

6. The turbine engine according to claim 5, characterized in that Further included is a compressor section and a flow conduit fluidly coupling the compressor section to the engine inlet.

7. The turbine engine according to claim 5, characterized in that Further included is an engine core disposed downstream of the inner center body and the outer center body.

8. The turbine engine according to claim 5, characterized in that in, The inner centerbody includes a plurality of first stage scavenging vanes configured to direct the first airflow having the momentum-leading particles toward the first stage inlet particle separator.

9. The turbine engine according to claim 5, characterized in that in, The outer centerbody includes a plurality of second stage scavenge vanes configured to direct the second air flow toward the second stage inlet particle separator.

10. The turbine engine according to claim 5, characterized in that in, The conduit has an outlet located outside the housing.

11. A method for separating particles from an air flow in a turbine engine, characterized in that The turbine engine has an inner center body, an outer center body radially spaced from the inner center body, and an outer shell radially spaced from the outer center body, the inner center body and the outer center body defining a first inlet duct therebetween, and the outer center body and the outer shell defining a second inlet duct therebetween, a first stage inlet particle separator disposed proximate the inner center body, and a second stage inlet particle separator disposed proximate the outer center body, the outer center body having an impact surface facing an engine inlet of the turbine engine, the method comprising: receiving an airflow comprising momentum-dominant particles and drag-dominant particles through the engine inlet; separating the airflow comprising the momentum-dominant particles and the drag-dominant particles into a first airflow comprising substantially momentum-dominant particles and a second airflow comprising drag-dominant particles; directing the first gas stream to the first stage inlet particle separator through the first inlet conduit; and directing the second gas stream to the second stage inlet particle separator through the second inlet conduit; The first stage inlet particle separator includes a duct that bypasses a flow duct configured to direct airflow to a compressor section of the turbine engine.

12. The method according to claim 11, characterized in that Further included directing a third gas flow comprising a substantially reduced particulate load to a compressor section disposed downstream of the inner center body and the outer center body.

13. The method according to claim 11, characterized in that in, Directing the first airflow toward the first stage inlet particle separator through the first inlet duct includes directing the first airflow having the momentum-dominant particles toward the first stage inlet particle separator using a plurality of first stage scavenging vanes disposed within the inner centerbody.

14. The method according to claim 11, characterized in that in, Directing the second airflow toward the second stage inlet particle separator through the second inlet duct includes directing the second airflow having drag-dominant particles toward the second stage inlet particle separator using a plurality of second stage scavenge vanes disposed within the outer centerbody.

15. The method according to claim 11, characterized in that Further included directing the first airflow through a first conduit, and directing the second airflow through a second conduit different from the first conduit.

16. The method according to claim 11, characterized in that Further included using a barrier filter to intercept particles not removed by the first stage inlet particle separator and the second stage inlet particle separator.

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