Patent Application
20250154896
The present disclosure relates to aircraft engines in general and to aircraft including mechanisms for removing entrained particles from an engine in particular.
Particles of various materials such as sand and dust and chemicals that enter a turbine engine can be harmful, for example potentially causing component surface erosion and/or corrosion, clogging of cooling holes and passages, to name a few. Particulate contamination primarily occurs at takeoff and landing due to the higher concentration of dirt particles near the ground. Typically, particles are only cleaned from the surfaces of the nacelle and the engine components, which leaves particles in the air that pass into the turbine engine. What is needed is an improved system for removing entrained particles from air passing within an aircraft turbine engine.
According to an aspect of the present disclosure, a method of removing particles entrained within an air flow that has entered a turbine engine disposed within a nacelle is provided. The turbine engine includes a fan section, a compressor section, a turbine section, and a bypass duct arranged along an axial centerline. The compressor and turbine sections are in communication with a core gas path. The bypass duct is disposed radially outside of the core gas path. The nacelle includes a nacelle inlet cavity disposed forward of the fan section. The nacelle inlet cavity defines an air inlet path into the turbine engine. The method includes providing a fluid injection system configured to inject a fluid into the air inlet path from a plurality of nozzles in communication with nacelle inlet cavity, and controlling the fluid injection system to inject the fluid into the air inlet path from the plurality of nozzles during at least one predetermined segment of an aircraft flight mission. The aircraft flight mission includes an idling segment, a taxiing segment, a take-off segment, an ascent segment, a descent segment, and a landing segment. Particles wetted by the injected fluid are subject to centrifugal force in and aft of the fan section and are directed radially outward for flow through the bypass duct.
In any of the aspects or embodiments described above and herein, the step of controlling the fluid injection system may include injecting the fluid into the air inlet path below a predetermined altitude value, and not injecting the fluid into the air inlet path above the predetermined altitude value.
In any of the aspects or embodiments described above and herein, a portion of the ascent segment and a portion of the descent segment are below the predetermined altitude value.
In any of the aspects or embodiments described above and herein, each nozzle has an ejection centerline, and the ejection centerline of each nozzle may be oriented to inject the fluid in a forward first direction that is parallel to the axial centerline of the turbine engine, or the ejection centerline of each nozzle may be oriented to inject the fluid in a radial second direction that is perpendicular to the axial centerline of the turbine engine, or the ejection centerline of each nozzle may be oriented to inject the fluid in a direction that is between the forward first direction and the radial second direction.
In any of the aspects or embodiments described above and herein, the plurality of nozzles may include at least one aft oriented nozzle that has an ejection centerline, and the ejection centerline of the aft oriented nozzle may be oriented to inject the fluid in an aft direction at an acute angle relative to a radial line extending perpendicular to the axial centerline.
In any of the aspects or embodiments described above and herein, the acute angle may be no greater than seventy degrees.
In any of the aspects or embodiments described above and herein, the plurality of nozzles may be spaced apart from one another around a circumference of the nacelle inlet cavity and may be disposed in a lower circumferential half of the nacelle inlet cavity.
In any of the aspects or embodiments described above and herein, the plurality of nozzles may be circumferentially spaced apart from one another and may be disposed in a lower circumferential half of the nacelle inlet cavity and in an upper circumferential half of the nacelle inlet cavity.
In any of the aspects or embodiments described above and herein, the plurality of nozzles may include a first subgroup of nozzles configured to inject the fluid into the air inlet path a first distance and a second subgroup of nozzles configured to inject the fluid into the air inlet path a second distance, wherein the first distance is greater than the second distance.
According to another aspect of the present disclosure, an aircraft is provided that includes a turbine engine, a nacelle, a fluid injection system, and a controller. The turbine engine has a fan section, a compressor section, a turbine section, and a bypass duct arranged along an axial centerline. The compressor section and the turbine section are in communication with a core gas path, and the bypass duct is disposed radially outside of the core gas path. The nacelle is configured to house the turbine engine. The nacelle includes a nacelle inlet cavity disposed forward of the fan section. The nacelle inlet cavity defines an air inlet path for air drawn into the turbine engine during operation of the turbine engine. The fluid injection system includes a plurality of nozzles in fluid communication with a fluid source. The nozzles are in communication with the nacelle inlet cavity. The nozzles are configured to inject a fluid into the air inlet path. The controller is in communication with the fluid injection system and a non-transitory memory storing instructions. The instructions when executed cause the controller to control the fluid source to provide the fluid to the nozzles for injection into the air inlet path during at least one predetermined segment of an aircraft flight mission. The aircraft flight mission includes an idling segment, a taxiing segment, a take-off segment, an ascent segment, a descent segment, and a landing segment. The turbine engine is configured such that particles entrained within the inlet air that are wetted by the injected fluid are directed to flow through the bypass duct.
In any of the aspects or embodiments described above and herein, the instructions when executed may cause the controller to control the fluid source to provide the fluid to the nozzles below a predetermined altitude value, and to not provide fluid to the nozzles above the predetermined altitude value.
In any of the aspects or embodiments described above and herein, the plurality of nozzles may be pivotally mounted.
In any of the aspects or embodiments described above and herein, the pivotally mounted nozzles may be controllable to pivot between a first positional orientation and a second positional orientation.
The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. For example, aspects and/or embodiments of the present disclosure may include any one or more of the individual features or elements disclosed above and/or below alone or in any combination thereof. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be understood, however, the following description and drawings are intended to be exemplary in nature and non-limiting.
During engine 20 operation, air enters the nacelle inlet cavity 64 and travels aft to the fan section 30. The inlet air is worked by the fan section 30. A portion of that worked air (“bypass air”) travels aft and enters the bypass duct 72 and provides a portion of the thrust produced by the engine 20. The remainder of the air worked by the fan section 30 enters the compressor inlet 68, subsequently entering the core gas path 74 through the compressor section 32, combustor section 34, and the turbine section 36 before exiting the engine 20. The terms “forward”, “leading”, “aft, “trailing” are used herein to indicate the relative position of a component or surface. As air passes through the engine 20, a “leading edge” of a stator vane or rotor blade encounters the air before the “trailing edge” of the same. In a conventional axial engine such as that shown in
The gas turbine engine 20 diagrammatically shown in
Embodiments of the present disclosure include an entrained particle removal system 76 (“EPRS”) that includes a fluid injection system 78 having a plurality of nozzles 80 and a fluid source 82. In some embodiments, the entrained particle removal system 76 may include a dedicated controller 84 or may be in communication with a shared controller that provides the functionality described herein with respect to entrainer particle removal system 76 as well as functionality for other engine 20 or aircraft systems. To facilitate the description herein, both the dedicated controller and the shared controller will be referred to as the “controller 84” and the present disclosure is not limited to either embodiment.
The nozzles 80 are configured to produce a distribution of fluid exiting the nozzles 80. The distribution may be in the form of a spray (e.g., a pattern of droplets-see
Referring to
The present disclosure is not limited to any particular nozzle 80 configuration other than one that is acceptable for the purposes described herein. In some system embodiments, all of the nozzles 80 may have the same configuration; e.g., a single configuration type. In some system embodiments, the nozzles 80 may include a plurality of different configuration types; e.g., some of the nozzles 80 may have a first configuration, while other nozzles 80 have a second configuration type. As a more specific example, in those system embodiments having a plurality of different nozzle 80 configuration types the system may include first nozzles 80 configured to propel a fluid a first maximum distance away from the nozzle 80, second nozzles 80 configured to propel a fluid a second maximum distance away from the nozzle 80, and so on, wherein the first and second maximum distances are different from one another; e.g., as diagrammatically shown in
The nozzles 80 are disposed in communication with nacelle inlet cavity 64; i.e., the nozzles 80 may be disposed in communication with a nacelle cavity portion of the leading edge panel 62 or the inlet panel 58, or any combination thereof.
The nozzles 80 may be disposed around a portion of the nacelle 22 circumference or around the entire nacelle 22 circumference.
The fluid source 82 may include a primary reservoir 92 (or reservoirs) for containing a volume of fluid for dispensing via the nozzles 80 and one or more fluid conduits 94 (e.g., tubing, piping, or the like) between the primary reservoir 92 and the nozzles 80. In some embodiments, the fluid source 82 may include one or more secondary reservoirs 96 (e.g., see
The controller 84 is in communication with entrained particle removal system 76 components such as the fluid source 82. In some system embodiments, the controller 84 may also be in communication with controllable fluid control hardware (e.g., valving, or the like), sensors, one the like. The controller 84 may be in communication with these components to control and/or receive signals therefrom to perform the functions described herein. The controller 84 may include any type of computing device, computational circuit, processor(s), CPU, computer, or the like capable of executing a series of instructions that are stored in memory. The instructions may include an operating system, and/or executable software modules such as program files, system data, buffers, drivers, utilities, and the like. The executable instructions may apply to any functionality described herein to enable the system to accomplish the same algorithmically and/or coordination of system components. The controller 84 includes or is in communication with one or more memory devices. The present disclosure is not limited to any particular type of memory device, and the memory device may store instructions and/or data in a non-transitory manner. Examples of memory devices that may be used include a computer readable storage medium, a read-only memory, random access memory, volatile memory, non-volatile memory, static memory, dynamic memory, flash memory, cache memory, and/or any device that stores digital information. The controller 84 may include, or may be in communication with, an input device that enables a user to enter data and/or instructions, and may include, or be in communication with, an output device configured, for example to display information, or to transfer data, etc. Communications between the controller 84 and other system components may be via a hardwire connection or via a wireless connection.
As will be described in detail herein, in some embodiments the entrained particle removal system 76 may be in communication with a bleed air valve 100 configured to bleed core gas from the compressor section 32. For example, some gas turbine engine 20 embodiments include a bleed air valve 100 disposed between the LPC 42 and the HPC 44 (e.g., see
The fluid may be any type of fluid that can be distributed and that will attach to particles entrained within the nacelle inlet air. The fluid attached to an entrained particle creates a “wetted particle” that is much heavier than the entrained particle itself. A non-limiting example of an acceptable fluid is water. In some instances, additives may be added to a fluid like water to enhance the functionality of the fluid; e.g., an additive that increases the propensity of the fluid to bind with and “wet” particles, or an additive that decreases the freezing temperature of the fluid, or an anti-corrosion additive, or the like, or any combination thereof. In those embodiments that include a secondary reservoir(s) 96, the additive fluid(s) may be disposed in the secondary reservoirs(s) 96. In an aircraft application where water may be produced or collected (e.g., a hydrogen-fueled engine, or an aircraft HVAC system, or the like), the produced or collected water may be directed to the primary reservoir 92 to replenish fluid as it is used.
In the operation of a turbine engine 20 (e.g., see
The present disclosure entrained particle removal system 76 provides a novel and unobvious system and method for removing entrained particles upstream of the engine 20 components where particulate fouling is problematic; i.e., engine hot section components that utilize cooling air. The present disclosure entrained particle removal system 76 is configured and controllable to inject fluid into the airflow passing through the nacelle inlet cavity 64 upstream of the fan section 30. The fluid initially stored in the reservoir(s) 92, 96 is provided to the nozzles 80. The structure 98 for providing the fluid (e.g., pump, pressurized reservoir, fluid valving, and the like) may be chosen for the application at hand and the present disclosure is not limited to any particular mechanism. The fluid is injected into the nacelle inlet cavity 64 via the nozzles 80 where it is incorporated with the inlet air flow. Some of the incorporated fluid will encounter particulate matter entrained within the airflow. Fluid encountering the particles will bind with the particles to form “wetted particles 102” having a mass greater than particles that have not been bound with fluid; i.e., “unwetted particles 104”. The specific binding process that occurs between particles 104 and fluid to form wetted particles 102 may vary as a function of the type of particulate matter, or the fluid, or environmental factors, or the like, or any combination thereof. Electrostatic attraction is a non-limiting example of a binding process that forms wetted particles 102. The present disclosure is not limited to any particular binding process for forming wetted particles 102.
The inlet air flow, now including wetted particles 102, enters and is worked by the fan section 30. Within and aft of the fan section 30, the inlet air worked by the fan section 30 will include a rotational component and an axial component. The wetted particles 102 (greater mass) within the rotating air flow are subject to centrifugal forces that force the wetted particles 102 radially outward as they travel axially aft. As indicated above and shown in
Inlet air flow will redirect the injected fluid in a direction axially into the engine 20. Embodiments of the present disclosure entrained particulate removal system 76 may be configured to inject fluid in a manner so that the fluid reaches different radial positions within the inlet air flow prior to being redirected axially to increase the probability that entrained particles within the airflow will encounter fluid and become wetted particles 102. Injecting fluid to different radial positions may be accomplished in a variety of different ways; e.g., spray nozzles 80 for a first radial distance (FRD) injection, first stream nozzles 80 that produce a first fluid velocity for a second radial distance (SRD) injection, and second stream nozzles 80 that produce a second fluid velocity (greater than the first fluid velocity) for a third radial distance (TRD) injection, where the third radial distance is greater than the second radial distance and the second radial distance is greater than the first radial distance (TRD>SRD>FRD).
In some embodiments, the present disclosure entrained particle removal system 76 may be in communication with a compressor bleed valve 100 configured to bleed core gas from the compressor section 32. The aforesaid bled core gas may be directed (e.g., see arrow 101) from the compressor section 32 and into the bypass duct 72 as diagrammatically shown in
The term “flight mission” is used herein to describe an entire operational mission of an aircraft; e.g., initial idling (with the aircraft stationary), taxiing, takeoff, ascent, cruise, descent, landing, return taxing, and the like. The term “takeoff” as used herein refers to ground travel of the aircraft that is intended to achieve liftoff from the ground. The term “landing” as used herein refers to ground travel of the aircraft after the aircraft has touched down to the ground.
The present disclosure entrained particle removal system 76 may be controlled to selectively inject fluid into the inlet air. For example, the system 76 may be controlled to inject fluid into the inlet air throughout a flight mission of an aircraft. Alternatively, the system may be controlled to inject fluid into the inlet air only during certain segments of a flight mission. It is understood that the potential to ingest entrained particles is greatest when the aircraft engine 20 is on the ground, to a lesser extent at lower altitude elevations, and to a significantly lesser extent above a predetermined altitude. The system 76 may be controlled to inject fluid in a manner that reflects the potential for ingesting particulate matter; e.g., the system 76 may be controlled to inject fluid (i.e., an “on mode”) into the inlet air during flight mission segments that are on the ground and possibly during flight at lower elevations (e.g., during initial idling, taxiing, takeoff, a portion of ascent, a portion of descent, landing, and return taxing) and not inject fluid (i.e., an “off mode”) during the remaining flight mission segments (e.g., cruise). In this manner, the fluid used for injection may be economized while at the same time the present disclosure system provides protection during the segments when particle entrainment is greatest. In some embodiments, the present disclosure entrained particle removal system 76 may be configured to inject fluid into the inlet air during flight mission segments that are on the ground and up to or below a predetermined altitude; e.g., during initial idle/taxi, takeoff, a portion of ascent, a portion of descent, landing, and return taxi) and not inject fluid above the predetermined altitude. These embodiments of the present disclosure are not limited to any particular predetermined altitude. The predetermined altitude vary geographically/regionally. The predetermined altitude may be selected based on information relating to the potential presence of entrained particles as a function of altitude.
In some embodiments, the present disclosure system 76 may be configured to control the volume of fluid injected; e.g., the system 76 may be configured to selectively inject fluid at a first volumetric flow rate, or at a second volumetric flow rate, and so on, wherein the first and second volumetric flow rates are different from one another.
The above-described examples of how the present disclosure system 76 may be configured to selectively control when fluid is injected, how much fluid is injected, and the like are provided to illustrate how the present disclosure system 76 may be configured and the present disclosure is not limited thereto.
While the principles of the disclosure have been described above in connection with specific apparatuses and methods, it is to be clearly understood that this description is made only by way of example and not as limitation on the scope of the disclosure. Specific details are given in the above description to provide a thorough understanding of the embodiments. However, it is understood that the embodiments may be practiced without these specific details.
It is noted that the embodiments may be described as a process which is depicted as a flowchart, a flow diagram, a block diagram, etc. Although any one of these structures may describe the operations as a sequential process, many of the operations can be performed in parallel or concurrently. In addition, the order of the operations may be rearranged. A process may correspond to a method, a function, a procedure, a subroutine, a subprogram, etc.
The singular forms “a,” “an,” and “the” refer to one or more than one, unless the context clearly dictates otherwise. For example, the term “comprising a specimen” includes single or plural specimens and is considered equivalent to the phrase “comprising at least one specimen.” The term “or” refers to a single element of stated alternative elements or a combination of two or more elements unless the context clearly indicates otherwise. As used herein, “comprises” means “includes.” Thus, “comprising A or B,” means “including A or B, or A and B,” without excluding additional elements.
It is noted that various connections are set forth between elements in the present description and drawings (the contents of which are included in this disclosure by way of reference). It is noted that these connections are general and, unless specified otherwise, may be direct or indirect and that this specification is not intended to be limiting in this respect. Any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option.
No element, component, or method step in the present disclosure is intended to be dedicated to the public regardless of whether the element, component, or method step is explicitly recited in the claims. No claim element herein is to be construed under the provisions of 35 U.S.C. 112 (f) unless the element is expressly recited using the phrase “means for.” As used herein, the terms “comprise”, “comprising”, or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
While various inventive aspects, concepts and features of the disclosures may be described and illustrated herein as embodied in combination in the exemplary embodiments, these various aspects, concepts, and features may be used in many alternative embodiments, either individually or in various combinations and sub-combinations thereof. Unless expressly excluded herein all such combinations and sub-combinations are intended to be within the scope of the present application. Still further, while various alternative embodiments as to the various aspects, concepts, and features of the disclosures—such as alternative materials, structures, configurations, methods, devices, and components, and so on—may be described herein, such descriptions are not intended to be a complete or exhaustive list of available alternative embodiments, whether presently known or later developed. Those skilled in the art may readily adopt one or more of the inventive aspects, concepts, or features into additional embodiments and uses within the scope of the present application even if such embodiments are not expressly disclosed herein. For example, in the exemplary embodiments described above within the Detailed Description portion of the present specification, elements may be described as individual units and shown as independent of one another to facilitate the description. In alternative embodiments, such elements may be configured as combined elements. It is further noted that various method or process steps for embodiments of the present disclosure are described herein. The description may present method and/or process steps as a particular sequence. However, to the extent that the method or process does not rely on the particular order of steps set forth herein, the method or process should not be limited to the particular sequence of steps described. As one of ordinary skill in the art would appreciate, other sequences of steps may be possible.
