Bearing with groove and production method thereof

Abstract

The invention discloses a bearing with a groove and a manufacturing method thereof. Examples disclosed herein include a bearing having a bearing surface with a groove, the bearing positioned adjacent a shaft, the groove facing the shaft; and a negative thermal expansion (NTE) material positioned in the recess, the NTE material at least partially filling the recess.

Description

Technical Field

[0001] The present disclosure relates generally to fluid pumps, and more particularly, to improved, more efficient pump design and operation. Background Art

[0002] Aircraft typically include various accessory systems that support the operation of the aircraft and / or its gas turbine engines. For example, such accessory systems may include a lubrication system that lubricates components of the engine, an engine cooling system that provides cooling air to engine components, an environmental control system that provides cooled air to the cabin of the aircraft, etc. Thus, during operation of these accessory systems, heat is added or removed from the fluid (e.g., oil, air, etc.). BRIEF DESCRIPTION OF THE DRAWINGS

[0003] Figure 1 is a side view of an example aircraft.

[0004] Figure 2 is a schematic cross-sectional view of an example gas turbine engine for an aircraft.

[0005] Figure 3 is a schematic diagram of an example thermal management system for transferring heat between fluids.

[0006] Figure 4 is a schematic diagram of an example heat transfer bus pump.

[0007] Figure 5 and Figure 6 Example components according to the teachings disclosed herein are shown.

[0008] Figure 7 An example radial bearing system according to the teachings disclosed herein is shown.

[0009] Figure 8-10 An example thrust bearing system according to the teachings disclosed herein is shown.

[0010] Figure 11-13 An example thrust plate according to the teachings disclosed herein is shown.

[0011] Fig.14 and Fig.15 An example bearing according to the teachings disclosed herein is shown.

[0012] Fig.16 is an example thrust bearing system in which the examples disclosed herein may be implemented.

[0013] Fig.17 is a flow chart representing an example method of manufacturing an example bearing or an example thrust plate disclosed herein.

[0014] The drawings are not drawn to scale. In general, the same reference numbers will be used throughout the drawings and accompanying written description to refer to the same or like parts. DETAILED DESCRIPTION

[0015] "Include" and "comprising" (and all their forms and tenses) are used as open-ended terms herein. Thus, whenever a claim adopts any form of "include" or "comprising" (e.g., includes, comprises, has, etc.) as a preamble or in any type of claim statement, it should be understood that additional elements, terms, etc. may be present without exceeding the scope of the corresponding claim or statement.

[0016] As used herein, the phrase "at least" when used as a transitional term, such as in the preamble of a claim, is open ended in the same manner as the terms "comprising" and "including" are open ended. The term "and / or," when used, for example, in a form such as A, B, and / or C, refers to any combination or subset of A, B, C, such as (1) A alone, (2) B alone, (3) C alone, (4) A and B, (5) A and C, (6) B and C, or (7) A and B and C. As used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A and B" is intended to refer to embodiments that include any of (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. Similarly, as used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A or B" is intended to refer to embodiments that include any of (1) at least one A, (2) at least one B, or (3) at least one A and at least one B.

[0017] As used herein in the context of describing the performance or execution of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A and B" is intended to refer to embodiments that include any of (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. Similarly, as used herein in the context of describing the performance or execution of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A or B" is intended to refer to embodiments that include any of (1) at least one A, (2) at least one B, or (3) at least one A and at least one B.

[0018] As used herein, singular references (e.g., "a", "a", "first", "second", etc.) do not exclude the plural. As used herein, the term "a" or "an" object refers to one or more of the object. The terms "a" (or "a"), "one or more", and "at least one" are used interchangeably herein. In addition, although listed separately, multiple devices, elements, or method actions can be implemented by, for example, the same entity or object. In addition, although individual features may be included in different examples or claims, these may be combined, and the inclusion of different examples or claims does not mean that the combination of features is not feasible and / or disadvantageous.

[0019] As used herein, unless otherwise indicated, connection references (e.g., attached, coupled, connected, and joined) may include intermediate members between the elements referred to by the connection reference and / or relative movement between those elements. Thus, a connection reference does not necessarily infer that two elements are directly connected and / or are in fixed relation to each other. As used herein, stating that any part is "in contact with" another part is defined to mean that there is no intermediate part between the two parts.

[0020] Unless otherwise specifically stated, descriptors such as "first," "second," "third," etc., used herein do not confer or otherwise indicate any meaning of priority, physical order, arrangement in a list, and / or ordering in any manner, but are merely used as labels and / or arbitrary names to distinguish elements to facilitate understanding of the disclosed examples. In some examples, the descriptor "first" may be used to refer to an element in the detailed description, while a different descriptor (such as "second" or "third") may be used in the claims to refer to the same element. In such cases, it should be understood that such descriptors are only used to clearly identify elements that may, for example, otherwise share the same name.

[0021] As used herein throughout the specification and claims, approximate language is applied to modify any quantitative representation that can be allowed to vary without causing a change in the basic function associated therewith. Therefore, a value modified by one or more terms such as "approximately", "approximately", and "substantially" is not limited to the specified precise value. In at least some cases, approximate language can correspond to the accuracy of an instrument used to measure a value, or the accuracy of a method or machine used to construct or manufacture a component and / or system. For example, approximate language can refer to within a ten percent margin.

[0022] The terms "front" and "rear" refer to relative positions within a gas turbine engine, pump, or vehicle, and refer to the normal operating attitude of the gas turbine engine, pump, or vehicle. For example, with respect to a gas turbine engine, the front refers to a position closer to the engine inlet, while the rear refers to a position closer to the engine nozzle or exhaust. Further, with respect to a pump, the front refers to a position closer to the pump inlet, while the rear refers to a position closer to the end of the pump opposite the inlet.

[0023] The terms "upstream" and "downstream" refer to relative directions relative to flow in a path. For example, with respect to fluid flow, "upstream" refers to the direction from which the fluid is flowing, while "downstream" refers to the direction toward which the fluid is flowing.

[0024] As used herein, the term "substantially orthogonal" in the context of describing the position and / or orientation of a first object relative to a second object includes the term orthogonal, and more broadly, includes the meaning that the first object is positioned and / or oriented relative to the second object at an absolute angle of no more than five degrees (5°) from orthogonal. For example, a first axis that is substantially orthogonal to a second axis is positioned and / or oriented relative to the second axis at an absolute angle of no more than five degrees (5°) from orthogonal.

[0025] As used herein, "axial" is used to refer to a position along the central axis of a rotating body. For example, the shaft of a pump is said to extend axially along the axis of rotation of the pump. As used herein, "radial" is used to refer to one or more points along a radial vector that originates from the central axis of the rotating body and points perpendicularly outward from the central axis. In some examples, the fluid is said to be accelerated radially outward from the impeller, which means that the fluid flows outward from the central axis (axis of rotation) of the impeller in a direction substantially orthogonal to the central axis. As used herein, "circumferential" is used to refer to a position along an arc or circle positioned at a radial distance from the central axis of the rotating body. For example, a thrust plate is referred to as having a channel positioned circumferentially along the thrust plate.

[0026] Centrifugal fluid pumps move fluid (e.g., fuel, water, oil, supercritical carbon dioxide (sCO2), etc.) through a system (e.g., a waste heat recovery (WHR) system) by converting the rotational kinetic energy of the impeller into the fluid kinetic energy of the flowing fluid. In other words, the angular velocity of the impeller is proportional to the flow rate of the flowing fluid leaving the pump. The impeller provides a change in rotational kinetic energy from the motor, which applies mechanical work to the impeller shaft coupled to the impeller and the rotor of the motor. The rotor is provided with a change in mechanical work (i.e., mechanical power) over a period of time from the stator in the motor, which applies an electromagnetic force to the rotor in the form of torque. When the motor supplies a constant amount of electrical energy to the stator, the rotor supplies a constant amount of mechanical energy to the impeller.

[0027] During operation of the pump, the rotation of the impeller shaft and the associated impeller causes the impeller shaft to vibrate radially within the pump's housing. A radial bearing (e.g., a hydrodynamic bearing, a foil bearing, a rolling element bearing, etc.) is framed inside the pump housing to support the radial load (e.g., weight) of the impeller shaft and damp the vibration.

[0028] In addition, during operation of the pump, the impeller shaft may experience an axial load that acts approximately parallel to the central axis of the pump and / or impeller shaft. The axial load acting on the impeller may be unbalanced, meaning that the front axial load (e.g., an axial load acting toward the front of the pump) and the rear axial load (e.g., an axial load acting toward the rear of the pump) may be unequal and produce an axial thrust of the impeller shaft. The front axial thrust or the rear axial thrust may cause the impeller shaft to move along the central axis and cause the portion coupled to the impeller shaft (e.g., an impeller, a rotor shaft, a motor armature, etc.) to contact the housing, the motor, and / or other internal portions of the pump. The pump housing includes an axial bearing (e.g., a hydrodynamic bearing, a foil bearing, etc.) that supports the axial thrust of the impeller shaft and reduces, suppresses, and / or damps such movement.

[0029] In some examples, the fluid (e.g., sCO2, oil, liquid helium, etc.) pressurized in the system by the pump can be used to lubricate radial and / or axial bearings to reduce friction between rotating elements within these bearings. For example, the pump can include a streamline leading from the pump outlet to the axial bearing to provide and / or transmit the pressurized fluid to the thrust bearing. As used herein, "streamline" can refer to the path of a fluid (e.g., flow path, flow direction, etc.) and / or a structure (e.g., a pipe, a housing, etc.) for surrounding (e.g., guiding, directing, etc.) a fluid.

[0030] The pressurized fluid flows between the thrust disc, the front thrust pad, and the rear thrust pad of the thrust bearing device, system, and / or assembly. The thrust disc is coupled to the impeller shaft and protrudes radially outward from the impeller shaft, and the thrust pad is coupled to the pump housing and protrudes radially inward toward the impeller shaft. In addition, the pump may include an ejector vane to drive the fluid from the inner portion of the pump housing to the pump outlet. In some examples, the ejector vane protrudes from the rear side of the impeller and plays a similar role to the impeller vane. That is, the fluid approaches the ejector vane along the central axis and is accelerated radially outward from the ejector vane. Therefore, the streamlines and ejector vanes can implement a lubrication circuit from the pump outlet to the axial bearing and back to the ejector vane to provide a continuous fluid flow to the axial load bearing.

[0031] During operation of the pump, the axial thrust of the impeller shaft can act in a forward direction or a rearward direction based on the interaction between the impeller blades / displacer blades and the fluid. The fluid enters through the pump inlet along the center / rotation / shaft axis toward the impeller, which includes impeller blades to accelerate the fluid radially outward into the pump outlet, chamber, streamline, housing, etc. The fluid pressure on the front side, end, face, etc. of the impeller can transmit a rear axial load to the impeller shaft in the rearward direction.

[0032] Similarly, fluid in the pump housing flows forward along the rotational axis of the impeller shaft and builds pressure on the back side, end, face, etc. of the impeller (e.g., displacer). The fluid pressure on the back side of the impeller can transfer a front load to the impeller shaft in a forward direction.

[0033] When the forward and rearward axial loads are equal in value and act in opposite directions, the pump is said to be "thrust balanced". As used herein, "forward thrust" refers to the unbalanced thrust acting in the forward direction on the impeller shaft due to the forward axial load exceeding the rearward axial load. As used herein, "rearward thrust" refers to the unbalanced thrust acting in the rearward direction on the impeller shaft due to the rearward axial load exceeding the forward axial load.

[0034] In some examples, when the pump is operated at a relatively low rotational speed, angular velocity, operating speed, etc. (e.g., 500, 1000, 2500 rpm, etc.), the fluid pressure at the pump inlet exceeds the fluid pressure within the pump housing. Thus, at relatively low operating speeds ("low speed"), a back thrust of the impeller shaft is induced.

[0035] In some examples, when the pump is operated at a relatively high rotational speed, angular velocity, operating speed, etc. (e.g., 5000, 10000, 25000 revolutions per minute (rpm), etc.), the fluid pressure within the pump housing exceeds the fluid pressure at the pump inlet. Thus, at relatively high operating speeds ("high speed"), a forward thrust of the impeller shaft is induced.

[0036] When forward thrust or backward thrust is applied to the impeller shaft, despite the axial support of the thrust bearing, it may occur that the impeller shaft is axially displaced (e.g., in a forward direction or a rearward direction) by a certain amount (e.g., 0.001, 0.005, 0.010 inches (in), etc.) from the initial position. At some operating speeds of the pump, the axial thrust acting on the impeller shaft may oscillate between the forward direction and the rearward direction. At such speeds, the thrust may oscillate at a frequency that known thrust bearings cannot adaptively and / or dynamically support or cannot support quickly, effectively and / or sufficiently. Example thrust bearings that cannot balance pressures may not maintain proper spacing between thrust pads, spacers, thrust disks, etc. In this case, damage to the thrust pads, thrust disks, impeller shaft or other pump components may result.

[0037] The example system disclosed herein reduces the amount of axial motion experienced by the impeller shaft due to forward thrust and backward thrust. The example bearing system disclosed herein can increase the interval between the impeller shaft and the radial bearing, the interval between the thrust plate and the corresponding thrust bearing, etc. Therefore, the example disclosed herein can reduce the frequency or amplitude of the impeller shaft or the part connected thereto physically contacting other parts and / or the housing of the pump. For example, the example disclosed herein adopts a negative thermal expansion (NTE) coating (e.g., material, insert, etc.) deposited in a groove to generate a gap between pump components (e.g., shaft, radial bearing, thrust plate, thrust bearing, thrust pad, etc.). In addition, the example system disclosed herein can improve the operating efficiency of a pump (e.g., a centrifugal sCO2 pump) by minimizing or otherwise reducing the friction energy loss associated with the axial impeller shaft movement. In addition, the example system disclosed herein can increase the time between maintenance services for repairing and / or replacing components of thrust bearings, motors, pumps, etc. The example disclosed herein is described as being used with a pump system. However, the example disclosed herein can be implemented in a compressor system, a turbine, a motor, a generator, a pump starter, a hydrogen pump system, etc.

[0038] For the drawings disclosed herein, the same numerals indicate the same elements throughout the drawings. Now referring to the drawings, Figure 1 is a side view of an example aircraft 10. Figure 1 As shown, the aircraft 10 includes a fuselage 12 and a pair of wings 14 (one shown) extending outwardly from the fuselage 12. In the example shown, a gas turbine engine 100 is supported on each wing 14 to propel the aircraft through the air during flight. In addition, the aircraft 10 includes a vertical stabilizer 16 and a pair of horizontal stabilizers 18 (one shown). However, in some examples, the aircraft 10 includes Figure 1 Illustrative examples of engines of different types and / or in different locations.

[0039] Additionally, the aircraft 10 may include a thermal management system 200 for transferring heat between fluids that support the operation of the aircraft 10. More specifically, the aircraft 10 may include one or more accessory systems that are configured to support the operation of the aircraft 10. For example, such accessory systems include a lubrication system that lubricates components of the engine 100, a cooling system that provides cooling air to components of the engine 100, an environmental control system that provides cooled air to a cabin of the aircraft 10, and the like. In such examples, the thermal management system 200 is configured to transfer heat from one or more fluids that support the operation of the aircraft 10 (e.g., oil of a lubrication system, air of a cooling system and / or environmental control system, and the like) to one or more other fluids that support the operation of the aircraft 10 (e.g., fuel supplied to the engine 100). However, in some other examples, the thermal management system 200 is configured to transfer heat between another fluid or component that supports the operation of the aircraft 10.

[0040] Although the examples disclosed herein are reference Figure 1 The aircraft 10 is described in detail, but the examples disclosed herein may be applicable to aircraft 10 used with Figure 1-3 The thermal management system 200 may be substantially similar to the thermal management system of another type or configuration of aircraft. Thus, the present subject matter may be readily adapted for use in another aircraft and / or another heat transfer application associated with another type of vehicle.

[0041] Figure 2 is a schematic cross-sectional view of an example gas turbine engine 100. In the example shown, the engine 100 is configured as a high bypass turbofan engine. However, in some examples, the engine 100 is configured as a propfan engine, a turbojet engine, a turboprop engine, a turboshaft gas turbine engine, etc.

[0042] In general, the engine 100 extends along an axial centerline 102 and includes a fan 104, a low pressure (LP) spool 106, and a high pressure (HP) spool 108 at least partially surrounded by an annular nacelle 110. More specifically, the fan 104 may include a fan rotor 112 and a plurality of fan blades 114 (one shown) coupled to the fan rotor 112. In this regard, the fan blades 114 are circumferentially spaced and extend radially outward from the fan rotor 112. In addition, the LP and HP spools 106, 108 are positioned downstream of the fan 104 along the axial centerline 102. As shown, the LP spool 106 is rotatably coupled to the fan rotor 112, which allows the LP spool 106 to rotate the fan blades 114. In addition, a plurality of outlet guide vanes or struts 116 are circumferentially spaced from each other and extend radially between a casing 118 surrounding the LP and HP spools 106, 108 and the nacelle 110. As such, struts 116 support nacelle 110 relative to outer shell 118 such that outer shell 118 and nacelle 110 define a bypass airflow passage 120 positioned therebetween.

[0043] Casing 118 generally surrounds or encloses a compressor section 122 , a combustion section 124 , a turbine section 126 , and an exhaust section 128 in serial flow order.

[0044] In some examples, the compressor section 122 includes a low pressure (LP) compressor 130 of the LP spool 106 and a high pressure (HP) compressor 132 of the HP spool 108 positioned downstream of the LP compressor 130 along the axial centerline 102. Each compressor 130, 132 may in turn include one or more rows of compressor stator vanes 134 interdigitated with one or more rows of compressor rotor blades 136. Thus, the compressors 130, 132 define a compressed air flow path 133 extending therethrough.

[0045] Additionally, in some examples, the turbine section 126 includes a high pressure (HP) turbine 138 of the HP spool 108 and a low pressure (LP) turbine 140 of the LP spool 106 positioned downstream of the HP turbine 138 along the axial centerline 102. Each turbine 138, 140 may in turn include one or more rows of turbine stator vanes 142 interdigitated with one or more rows of turbine rotor blades 144.

[0046] In addition, the LP spool 106 includes a low pressure (LP) shaft 146, and the HP spool 108 includes a high pressure (HP) shaft 148 positioned concentrically about the LP shaft 146. In such an example, the HP shaft 148 rotatably couples the turbine rotor blades 144 of the HP turbine 138 and the compressor rotor blades 136 of the HP compressor 132, such that rotation of the turbine rotor blades 144 of the HP turbine 138 rotatably drives the compressor rotor blades 136 of the HP compressor 132. As shown, the LP shaft 146 is directly coupled to the turbine rotor blades 144 of the LP turbine 140 and the compressor rotor blades 136 of the LP compressor 130. In addition, the LP shaft 146 is coupled to the fan 104 via a gearbox 150. In this regard, rotation of the turbine rotor blades 144 of the LP turbine 140 rotatably drives the compressor rotor blades 136 of the LP compressor 130 and the fan blades 114.

[0047] In some examples, the engine 100 generates thrust to propel the aircraft. More specifically, during operation, air 152 enters an inlet portion 154 of the engine 100. The fan 104 supplies a first portion 156 of the air 152 to the bypass airflow passage 120 and a second portion 158 of the air 152 to the compressor section 122. The second portion 158 of the air 152 first flows through the LP compressor 130, where the compressor rotor blades 136 gradually compress the second portion 158 of the air 152. Next, the second portion 158 of the air 152 flows through the HP compressor 132, where the compressor rotor blades 136 continue to gradually compress the second portion 158 of the air 152. The compressed second portion 158 of the air 152 is then delivered to the combustion section 124. In the combustion section 124, the second portion 158 of the air 152 is mixed with fuel and combusted to generate high temperature and high pressure combustion gases 160. Thereafter, the combustion gases 160 flow through the HP turbine 138, wherein turbine rotor blades 144 of the HP turbine 138 extract a first portion of kinetic and / or thermal energy from the combustion gases 160. This energy extraction rotates the HP shaft 148, which drives the HP compressor 132. The combustion gases 160 then flow through the LP turbine 140, wherein turbine rotor blades 144 of the LP turbine 140 extract a second portion of kinetic and / or thermal energy from the combustion gases 160. This energy extraction rotates the LP shaft 146, which drives the LP compressor 130 and the fan 104 via the gearbox 150. The combustion gases 160 then exit the engine 100 through the exhaust section 128.

[0048] As described above, the aircraft 10 may include a thermal management system 200 for transferring heat between fluids that support the operation of the aircraft 10. In this regard, the thermal management system 200 may be located within the engine 100. For example, Figure 2As shown, the thermal management system 200 is positioned within the housing 118 of the engine 100 . However, in some other examples, the thermal management system 200 is positioned at another location within the engine 100 .

[0049] Additionally, in some examples, the engine 100 defines a third stream flow path 170. Generally, the third stream flow path 170 extends from the compressed air flow path 133 defined by the compressor section 122 to the bypass air flow passage 120. In this regard, the third stream flow path 170 allows a portion of the second portion 158 of the air 152 from the compressor section 122 to bypass the combustion section 124. More specifically, in some examples, the third stream flow path 170 defines a concentric or non-concentric passage with respect to the compressed air flow path 133 downstream of one or more of the compressors 130, 132, or the fan 104. The third stream flow path 170 can be configured to selectively remove the second portion 158 of the air 152 from the compressed air flow path 133 via one or more variable guide vanes, nozzles, or other actuatable flow control structures.

[0050] Additionally, as will be described below, in some examples, the thermal management system 200 transfers heat to the air flowing through the third stream flow path 170. However, the pressure and / or flow rate of the fluid (e.g., a heat exchange fluid, such as a supercritical fluid (e.g., sCO2, etc.)) within the thermal management system 200 limits the rate at which thermal energy can be transferred between the air and the heat exchange fluid. Additionally, it is advantageous for the thermal management system 200 to generate the pressure and / or flow rate using a pump that supports the axial thrust of a shaft within the pump to increase the life and / or efficiency of the pump and the thermal management system 200.

[0051] Although the examples disclosed herein are reference Figure 2 The gas turbine engine 100 is described in detail, but the examples disclosed herein may be applicable to use with Figure 1-3 The thermal management system 200 may be substantially similar to the thermal management system of another type or configuration of an engine. Thus, the present subject matter may be readily adapted for use with another engine and / or another heat transfer application associated with another type of vehicle.

[0052] Figure 3 is a schematic diagram of an example implementation of a thermal management system 200 for transferring heat between fluids. In general, the thermal management system 200 is as described above and in Figure 1 and Figure 2 1 and 10. However, the thermal management system 200 may be implemented within another type of aircraft and / or another gas turbine engine of another configuration.

[0053] As shown, the thermal management system 200 includes a heat transfer bus 202. Specifically, in some examples, the heat transfer bus 202 is configured as one or more fluid conduits through which a fluid (e.g., a heat exchange fluid) flows. As described below, the heat exchange fluid flows through various heat exchangers so that heat is added to the heat exchange fluid and / or removed from the heat exchange fluid. In this regard, the heat exchange fluid can be a working fluid, such as sCO2, oil, liquid helium, etc. In addition, in such an example, the thermal management system 200 includes a pump 204 configured to pump the heat exchange fluid through the heat transfer bus 202.

[0054] In addition, the thermal management system 200 includes one or more heat source heat exchangers 206 arranged along the heat transfer bus 202. More specifically, the heat source heat exchangers 206 are fluidly coupled to the heat transfer bus 202 such that a heat exchange fluid flows through the heat source heat exchangers 206. In this regard, the heat source heat exchangers 206 are configured to transfer heat from a fluid supporting the operation of the aircraft 10 to the heat exchange fluid, which cools the fluid supporting the operation of the aircraft 10. Thus, the heat source heat exchangers 206 add heat to the heat exchange fluid. Although Figure 3 Two heat source heat exchangers 206 are shown, but the thermal management system 200 may include a single heat source heat exchanger 206 or three or more heat source heat exchangers 206 .

[0055] The heat source heat exchangers 206 may correspond to heat exchangers of many configurations that cool fluids that support the operation of the aircraft 10. In some examples, at least one of the heat source heat exchangers 206 is a heat exchanger of a lubrication system of the engine 100. In such an example, the heat source heat exchangers 206 transfer heat from oil that lubricates the engine 100 to a heat transfer fluid. In some other examples, at least one of the heat source heat exchangers 206 is a heat exchanger of a cooling system of the engine 100. In such an example, the heat source heat exchanger 206 transfers heat from cooling air exhausted from the compressor section 122 (or compressor discharge plenum) of the engine 100 to a heat transfer fluid. However, in some other examples, the heat source heat exchangers 206 correspond to other types of heat exchangers that cool fluids that support the operation of the aircraft 10.

[0056] In addition, the thermal management system 200 includes a plurality of radiator heat exchangers 208 arranged along the heat transfer bus 202. More specifically, the radiator heat exchangers 208 are fluidly coupled to the heat transfer bus 202 such that a heat exchange fluid flows through the radiator heat exchangers 208. In this regard, the radiator heat exchangers 208 are configured to transfer heat from the heat exchange fluid to other fluids supporting the operation of the aircraft 10, which heats the other fluids supporting the operation of the aircraft 10. Thus, the radiator heat exchangers 208 remove heat from the heat exchange fluid. Although Figure 3Two radiator heat exchangers 208 are shown, but the thermal management system 200 may include three or more radiator heat exchangers 208 .

[0057] The radiator heat exchangers 208 may correspond to many configurations of exchangers that heat fluids that support the operation of the aircraft 10. For example, at least one of the radiator heat exchangers 208 is a heat exchanger of a fuel system of the engine 100. In such an example, the radiator heat exchangers 208 transfer heat from a heat transfer fluid to the fuel supplied to the engine 100. In some other embodiments, at least one of the radiator heat exchangers 208 is a heat exchanger that contacts the first portion 156 of the air 152 flowing through the bypass airflow passage 120 of the engine 100. In such an example, the radiator heat exchangers 208 transfer heat from the heat transfer fluid to the first portion 156 of the air 152 flowing through the bypass airflow passage 120.

[0058] In some examples, one or more of the radiator heat exchangers 208 are configured to transfer heat to the air flowing through the third stream flow path 170. In such examples, the radiator heat exchangers 208 are connected to the air flowing through the third stream flow path 170 ( Figure 2 ) of the air of the third stream flow path 170. Therefore, the heat from the heat exchange fluid flowing through the heat transfer bus 202 can be transferred to the air flowing through the third stream flow path 170. Using the third stream flow path 170 as a radiator of the thermal management system 200 provides one or more technical advantages. For example, the third stream flow path 170 provides greater cooling than other bleed air sources because a larger volume of air flows through the third stream flow path 170 compared with other bleed air flow paths. In addition, the air flowing through the third stream flow path 170 is colder than the air flowing through other bleed air flow paths and the compressor bleed air. In addition, the air in the third stream flow path 170 is pressurized, which allows the radiator heat exchanger 208 to be smaller than the heat exchanger that relies on other radiators in the engine 100. In addition, in the example where the engine 100 is non-ducted, different from using ambient air (e.g., a heat exchanger in contact with the air flowing around the engine 100), using the third stream flow path 170 as a radiator will not increase the resistance on the engine 100. However, in some other examples, radiator heat exchanger 208 corresponds to other types of heat exchangers that heat fluids that support operations of aircraft 10 .

[0059] Additionally, in some examples, the thermal management system 200 includes one or more bypass conduits 210. Specifically, as shown, each bypass conduit 210 is fluidly coupled to the heat transfer bus 202 such that the bypass conduit 210 allows at least a portion of the heat exchange fluid to bypass one of the heat exchangers 206, 208. In some examples, the heat exchange fluid bypasses one or more of the heat exchangers 206, 208 to adjust the temperature of the heat exchange fluid within the heat transfer bus 202. The example heat exchange fluid flow through the bypass conduits 210 is controlled to adjust the pressure of the heat exchange fluid within the heat transfer bus 202. Figure 3 In the example shown, each heat exchanger 206, 208 has a corresponding bypass conduit 210. However, in some other examples, other numbers of heat exchangers 206, 208 may have corresponding bypass conduits 210 as long as at least one bypass conduit 210 is present.

[0060] Additionally, in some examples, the thermal management system 200 includes one or more heat source valves 212 and one or more radiator valves 214. Generally, each heat source valve 212 is configured to control the flow of a heat exchange fluid through a bypass conduit 210 that bypasses the heat source heat exchanger 206. Similarly, each radiator valve 214 is configured to control the flow of a heat exchange fluid through a bypass conduit 210 that bypasses the radiator heat exchanger 208. In this regard, each valve 212, 214 is fluidly coupled to the heat transfer bus 202 and a corresponding bypass conduit 210. Thus, each valve 212, 214 can be moved between fully and / or partially open and / or closed positions to selectively block heat exchange flow through its corresponding bypass conduit 210.

[0061] The valves 212, 214 are controlled based on the pressure of the heat exchange fluid within the heat transfer bus 202. More specifically, as indicated above, in some cases, the pressure of the heat exchange fluid flowing through the heat transfer bus 202 may fall outside the desired pressure range. When the pressure of the heat exchange fluid is too high, the thermal management system 200 may cause accelerated wear. In this regard, when the pressure of the heat exchange fluid within the heat transfer bus 202 exceeds the maximum or otherwise increased pressure value, one or more heat source valves 212 are opened. In this example, at least a portion of the heat exchange fluid flows through the bypass conduit 210 instead of the heat source heat exchanger 206. Therefore, less heat is added to the heat exchange fluid through the heat source heat exchanger 206, which reduces the temperature of the fluid and thus reduces the pressure of the fluid. In some examples, the maximum pressure value is between 3800 psi and 4000 psi or less. In some examples, the maximum pressure value is between 2700 psi and 2900 psi, such as 2800 psi. In some other examples, the maximum pressure value is between 1300 psi and 1500 psi, such as 1400 psi. Such a maximum pressure value substantially prevents thermal management system 200 from causing accelerated wear.

[0062] In some examples, the maximum pressure value is set prior to and / or during operation based on one or more parameters associated with the thermal management system 200 (e.g., materials used, pump 204 design, aircraft 10 design, gas turbine engine 100 design, heat exchange fluid, etc.) The example maximum pressure value can be adjusted relative to the pressure capacity of the heat transfer bus 202, the pump 204, the heat exchangers 206, 208, the bypass conduit 210, and / or the valves 212, 214.

[0063] In contrast, when the pressure of the heat exchange fluid is too low, the pump 204 may experience operability problems and increased wear. Thus, when the pressure of the heat exchange fluid in the heat transfer bus 202 drops to a pressure value below the minimum pressure value or otherwise reduced, one or more of the radiator valves 214 are opened. In this example, at least a portion of the heat exchange fluid flows through the bypass conduit 210 instead of the radiator heat exchanger 208. Therefore, less heat is removed from the heat exchange fluid by the radiator heat exchanger 208, which increases the temperature of the fluid and thus increases the pressure of the fluid. In some examples, the minimum pressure value is 1070 psi or greater. In some examples, the minimum pressure value is between 1150 psi and 1350 psi, such as 1250 psi. In some other examples, the minimum pressure value is between 2400 psi and 2600 psi, such as 2500 psi. This minimum pressure value is typically used when the heat exchange fluid is in a supercritical state (e.g., when the heat exchange fluid is carbon dioxide).

[0064] Thus, the thermal management system 200 can be configured to operate such that the pressure of the heat transfer fluid is maintained within a range extending between a minimum pressure value and a maximum pressure value. In some examples, the range extends from 1070 psi to 4000 psi. Specifically, in one example, the range extends from 1250 psi to 1400 psi. In some other examples, the range extends from 2500 psi to 2800 psi.

[0065] Thus, the operation of the pump 204 and valves 212 , 214 allows the disclosed thermal management system 200 to maintain the pressure of the heat exchange fluid within the heat transfer bus 202 within a specified range of values ​​as the thermal load imposed on the thermal management system 200 changes.

[0066] In addition, an example pump 204 drives the heat exchange fluid through the thermal management system 200. In some examples, the thermal management system 200 includes one pump 204 or multiple pumps 204, depending on the desired flow rate, the delta pressure on the pump 204, and / or the kinetic energy loss of the heat exchange fluid in the heat transfer bus 202. For example, the pump 204 can increase the output head to accelerate the flow of the heat exchange fluid to a first flow rate. As the heat exchange fluid passes through the heat transfer bus 202, the example kinetic energy of the heat exchange fluid is dissipated due to friction, temperature changes, etc. Due to the kinetic energy loss, the heat exchange fluid is decelerated to a second flow rate at a point upstream of the pump 204. When the example second flow rate is lower than the desired operating flow rate of the heat exchange fluid, the pump 204 can be a different architecture that outputs a higher first flow rate, or one or more additional pumps 204 can be included in the thermal management system 200.

[0067] Figure 4 is an example heat transfer bus pump 400 (e.g., sCO2 pump, Figure 3 A schematic diagram of a pump 204, etc. Figure 4 In the illustrated example, a heat transfer bus pump 400 drives a heat exchange fluid (such as sCO 2 ) through one or more fluid conduits 402 (eg, Figure 3 Specifically, the heat exchange fluid flows through an inlet pipe 404 and encounters an impeller 406 (e.g., a compressor wheel), which rotates to drive the heat exchange fluid through a pump outlet 408 that is fluidly coupled to the fluid conduit 402. In turn, the fluid conduit 402 can supply the heat exchange fluid to one or more heat exchangers (e.g., Figure 3 heat exchangers 206, 208). Thus, the heat transfer bus pump 400 can pump heat exchange fluid to manage Figure 1 The aircraft 10 and / or Figure 2 of the working fluid associated with the gas turbine engine 100 .

[0068] exist Figure 4 In the example shown, the heat transfer bus pump 400 includes a motor 410 positioned in a motor housing 412. Figure 4 4, the motor 410 is an induction motor operably coupled to a variable frequency drive (VFD) and a control circuit (not shown) (such as a full authority digital engine controller (FADEC)) that controls the speed of the motor 410. For example, the control circuit can operate the motor 410 based on the pressure and / or temperature of the heat exchange fluid in the fluid conduit 402 and / or the heat transfer bus pump 400. In some examples, the control circuit can operate the motor 410 based on the pressure and / or temperature of the working fluid affected by the heat exchange fluid. Additionally or alternatively, the control circuit can operate the motor 410 based on vibration measurements obtained by an accelerometer operably coupled to the heat transfer bus pump 400 and / or the fluid conduit 402.

[0069] exist Figure 4 4, the motor housing 412 is at least partially surrounded by a cooling jacket 414 to prevent the motor 410 from overheating. The rear end of the motor housing 412 is coupled to the rear bearing housing 416 via a first bolt 418. In addition, the end cap 420 is coupled to the rear bearing housing 416 via the first bolt 418. The front end of the motor housing 412 is coupled to a front bearing housing 422 opposite to the rear bearing housing 416 via a second bolt 424. In addition, the front bearing housing 422 is coupled to a back plate 426 and a pump outlet 408 on the opposite side of the back plate 426 via the second bolt 424.

[0070] exist Figure 4In the example shown, the motor 410 includes a stator 428 to induce alternating current in the field coil and emit an alternating magnetic field around the central axis of the motor 410. The alternating magnetic field interacts with the permanent magnets of the rotor 430, thereby providing torque to the rotor 430. The rotor 430 is fixedly coupled to an impeller shaft 432 ("shaft 432"), and the shaft is fixedly coupled to the impeller 406. In this way, the motor 410 drives the rotation of the shaft 432, which in turn drives the rotation of the impeller 406. The rear end of the shaft 432 is supported by a first radial foil bearing 434 coupled to the rear bearing housing 416. Similarly, the front end of the shaft 432 is supported by a second radial foil bearing 436 coupled to the front bearing housing 422.

[0071] The first radial foil bearing 434 and the second radial foil bearing 436 include spring-loaded foil journal bushings that support the radial load of the shaft 432 during relatively low (e.g., startup) rotational speeds (e.g., 0-5000 revolutions per minute (rpm), etc.). When the motor 410 rotates the shaft 432 at relatively high (e.g., operating) rotational speeds (e.g., 5000-20000 rpm, etc.), the pressure of the working medium (e.g., air, oil, sCO2, etc.) increases and pushes the foil bushings radially outward. Therefore, when the shaft 432 rotates at operating speeds (e.g., 3000 rpm, 10000 rpm, 25000 rpm, etc.), the pressurized working medium supports the radial load of the shaft 432.

[0072] exist Figure 4 In some examples, the thrust disk 438 of the shaft 432 is supported by a thrust bearing system 440. For example, the thrust bearing system 440 may include a foil bearing to support the axial load of the shaft 432 via interaction with the thrust disk 438. In some examples, the thrust bearing system 440 is coupled to the rear bearing housing 416 and / or the end cap 420 via bolts.

[0073] The example impeller 406 of the heat transfer bus pump 400 includes ejector vanes 442 on the rear portion of the impeller 406. At the operating speed of the motor 410, the ejector vanes 442 cause the working fluid (e.g., sCO2) to flow forward into the fluid conduit 402 from the front bearing housing 422, the motor housing 412, etc.

[0074] exist Figure 4In the illustrated example, an example sCO2 fluid flows into the heat transfer bus pump 400 through the fluid conduit 402, as indicated by the arrow indicating the flow direction 444. At a low speed (e.g., a starting speed) of the motor 410, the flow direction 444 of the example sCO2 exerts a back thrust 446 on the impeller 406 and the shaft 432, as indicated by the arrow indicating the direction of the back thrust 446. At a high speed (e.g., an operating speed) of the motor 410, the ejector vanes 442 drive the heat exchange fluid within the heat transfer bus pump 400 forward toward the pump outlet 408, and the fluid generates a forward thrust 448 on the impeller 406 and the shaft 432, as indicated by the arrow indicating the direction of the forward thrust 448. A thrust bearing system 440 is included in the heat transfer bus pump 400 to support the back thrust 446 and the forward thrust 448 of the shaft 432.

[0075] In some examples, the heat transfer bus pump 400 includes an example outer flow line 450 that branches from the pump outlet 408 to provide sCO2 as a working medium to the thrust bearing system 440 and support the thrust disk 438 when pressurized. Additionally or alternatively, the outer flow line 450 branches from the fluid conduit 402 and / or the ejector vane 442. The example outer flow line 450 can bypass one or more of the motor housing 412, the rear bearing housing 416, the front bearing housing 422, and / or the back plate 426 to approach the thrust bearing system 440.

[0076] In some examples, the heat transfer bus pump 400 includes an example inner flow line 452 that branches from the ejector vane 442 to provide sCO2 as a working medium to the thrust bearing system 440 and support the thrust disk 438 when pressurized. Additionally or alternatively, the inner flow line 452 branches from the fluid conduit 402 and / or the pump outlet 408. The example inner flow line 452 can pass through one or more of the motor housing 412, the rear bearing housing 416, the front bearing housing 422, and / or the back plate 426 to access the thrust bearing system 440.

[0077] Figure 4 The outer streamlines 450 and inner streamlines 452 are shown as example configurations to reflect the approximate location of the streamlines and the direction of flow. Figure 4 4 shows an outer flow line 450 and an inner flow line 452, but only one may be included in the heat transfer bus pump 400 to achieve the same function. The heat transfer bus pump 400 may be configured with an outer flow line 450 to reduce complexity during manufacturing and / or assembly and reduce the risk of internal leaks. The heat transfer bus pump 400 may be configured with an inner flow line 452 to reduce the amount of space occupied by the heat transfer bus pump 400. Figure 4 Also shown in FIG. 4 are first return flow lines 454 and second return flow lines 456 to generally depict the exit point and flow direction of the working fluid from the thrust bearing system 440 to the ejector vanes 442 .

[0078] exist Figure 4 In the example shown, the thrust disk 438 and the thrust bearing system 440 are designed so that the front and rear bearing capacities are not dynamically adjusted to account for fluctuations between the rear thrust 446 and the front thrust 448. In other words, there may be no dynamic subsystem in the thrust bearing system 440 to dynamically change the axial support of the front or rear side of the thrust disk 438 in response to the transition from the rear thrust 446 to the front thrust 448, and vice versa. The examples disclosed herein include devices and systems that dynamically support axial loads (e.g., the rear thrust 446 and / or the front thrust 448) in the forward direction and / or the rearward direction based on changes in fluid pressure on the front and rear sides of the thrust disk. In addition, the example radial foil bearings 434, 436 are designed so that low rotational speeds of the shaft 432 may not generate sufficient hydrodynamic lift between the shaft 432 and the radial foil bearings 434, 436. In other words, at low operating speeds, there may be little clearance (e.g., spacing) between the shaft 432 and each of the radial foil bearings 434, 436, which may result in wear or damage to the shaft 432, the first radial foil bearing 434, the second radial foil bearing 436, etc. The examples disclosed herein include devices and systems that support low or high rotational speeds of an example impeller shaft.

[0079] Figure 5 and Figure 6 5 shows a cross-sectional view of an example assembly 500 constructed according to the teachings disclosed herein. The example assembly 500 includes an example bearing (e.g., bearing portion) 502 adjacent to an example shaft (e.g., shaft portion) 504. In some examples, the bearing 502 can be implemented as a foil bearing 434, 436 ( Figure 4 ), and the axis 504 may be implemented as the axis 432 ( Figure 4 In some examples, bearing 502 may be implemented as thrust bearing system 440 ( Figure 4 ) in at least one of the foil bearings, and the shaft 504 may be implemented as a thrust disk 438 ( Figure 4 ).in other words, Figure 5 and Figure 6 The assembly 500 may include the Figure 4 An example heat transfer bus pump 400 is shown.

[0080] The example bearing 502 includes a first example surface (eg, bearing surface) 506 opposite a second example surface 508. The first example surface 506 includes an example recess (also referred to as a cavity, depression, dimple, etc.) 510. Figure 5 and Figure 6In the example, the first example surface 506 is the inner surface of the bearing 502 facing the shaft 504. The example groove 510 faces the shaft 504. In some examples, the first surface 506 can at least partially surround the example longitudinal axis 512 of the assembly 500. In this example, the shaft 504 is aligned with the longitudinal axis 512. Figure 5 and Figure 6 As shown, the example groove 510 extends from the first surface 506 toward the second surface 508. In some examples, the groove 510 can extend in a radial direction from the first surface 506 to the second surface 508. The example assembly 500 includes four grooves 510. However, the example assembly 500 can include any number of grooves (e.g., at least one, two, three, five, etc.).

[0081] In some examples, bearing 502 is a radial bearing around shaft 504, as described below in conjunction with at least Figure 7 , Fig.14 and Fig.15 Additionally or alternatively, the example bearing 502 can be implemented as a thrust bearing (e.g., a thrust pad) around an example thrust disk. In such an example, the example shaft 504 can be implemented as an example thrust disk, as described below in at least combination with Figure 8-13 and Fig.16 Described in detail.

[0082] The example assembly 500 includes an example NTE material (eg, coating) 514 positioned (eg, deposited) in each of the grooves 510. Figure 5 and Figure 6 As shown, the example NTE material 514 at least partially fills each of the grooves 510. In some examples, the NTE material 514 is coated (e.g., covers) on the inner surface (e.g., one or more walls) of the grooves 510. In addition, the example grooves 510 include approximately equal (e.g., within .5 microns (μ)) amounts or depths of the NTE material 514. However, each of the example grooves 510 can include a different amount of the NTE material 514. For example, a first groove in the grooves 510 can include a 1 micron depth of the NTE material 514, a second groove in the grooves 510 can include a 2 micron depth of the NTE material 514, and so on. In some examples, the NTE material 514 includes at least one of zirconium tungstate (Zr(WO4)2), zirconium vanadate (ZrV2O7), or niobium titanium (Nb-Ti).

[0083] like Figure 5As shown, the example bearing 502 can contact (e.g., rub) the example shaft 504 during operation. For example, when the shaft 504 rotates (e.g., in a range from 12,000 revolutions per minute (rpm) to 17,000 rpm), contact between the bearing 502 and the shaft 504 can occur. Such contact or rotation can increase heat transfer (e.g., relative temperature, windage heating, etc.) between the bearing 502 and the shaft 504. In some examples, when the shaft 504 is angled or tilted toward the bearing 502, contact between the shaft 504 and the bearing 502 can occur.

[0084] exist Figure 5 , the example groove 510 can be partially filled with the NTE material 514 such that the groove 510 includes (e.g., contains) a fluid (e.g., air) and the NTE material 514. The example NTE material 514 shrinks (e.g., contracts, decreases in size, etc.) in response to an increase in temperature (e.g., when the bearing 502 contacts a moving ambient hot fluid). In this example, the shrinkage of the NTE material 514 allows the fluid to enter the groove 510 and push against the NTE material 514, the walls of the groove 510, and the bearing 502 to induce a gap (e.g., a fluid film, a hydrodynamic lift force, etc.) between the bearing 502 and the shaft 504 (e.g., a fluid film, a hydrodynamic lift force, etc.) Figure 6 In other words, the increase in heat transfer between the bearing 502 and the shaft 504 causes the NTE material 514 to shrink, which in turn enables fluid to flow into and out of the groove 510, so that a fluid film is formed between the bearing 502 and the shaft 504. Therefore, Figure 5 and Figure 6 The example assembly 500 can generate a fluid air gap in response to contact / friction between the bearing 502 and the shaft 504. In addition, Figure 5 and Figure 6 The example assembly 500 can limit or prevent heat transfer between the bearing 502 and the shaft 504, which improves the performance and life of the assembly 500. In some examples, the fluid film induced between the shaft 504 and the bearing 502 can balance or level the shaft 504 within the assembly 500.

[0085] In response to the elevated local temperature (eg, 273 Kelvin (K) to 1400 K) generated by contact between the bearing 502 and the shaft 504, the NTE material 514 is increased in size from the first size ( Figure 5 ) is reduced to a second size ( Figure 6504 and 502). In some examples, each of the grooves 510 may include approximately the same amount (e.g., within .5 microns) of NTE material 514 after the NTE material 514 shrinks. However, each of the grooves 510 may include a different amount of NTE material 514 after the NTE material 514 shrinks. For example, a first groove in the grooves 510 may be positioned closer to a high temperature area of ​​the assembly 500 (e.g., an area prone to contact between the shaft 504 and the bearing 502), and a second groove in the grooves 510 may be positioned further away from the high temperature area. Prior to shrinkage, the example NTE material 514 positioned in the first groove in the grooves 510 and the example NTE material 514 positioned in the second groove in the grooves 510 may both be 2 microns. The NTE material 514 positioned in a first groove of the grooves 510 may shrink from 2 microns to 0.5 microns (e.g., shrink by 1.5 microns) in response to an increase in temperature, while the NTE material 514 positioned in a second groove of the grooves 510 may shrink from 2 microns to 1.5 microns (e.g., shrink by 0.5 microns). Therefore, after a fluid film is formed based on the proximity of the first groove of the grooves 510 to the high temperature region, a greater amount of NTE material 514 may be present in the second groove of the grooves 510 than in the first groove of the grooves 510.

[0086] Figure 7 An axial view of an example assembly 700 constructed in accordance with the teachings disclosed herein is shown. Example assembly 700 includes an example radial bearing 702 ("bearing 702") about an example shaft 704. Example radial bearing 702 includes example grooves 706 having example NTE material 708 disposed therein. Example assembly 700 includes twelve grooves 706. However, example assembly 500 may include any number of grooves (e.g., two, ten, fifteen, etc.). Figure 7 As shown in the example of the embodiment of the present invention, each of the grooves 706 can include a different amount of NTE material 708. In addition, the example NTE material 708 can be positioned at different locations within each of the grooves 706. For example, a first groove 706a in the example grooves includes NTE material 708 positioned at an example vertex 710 of the groove 706a. In addition, a second groove 706b in the example grooves includes NTE material 708 positioned at an example wall 712 of the groove 706b. In this example, the grooves 706 are positioned on an example inner surface 714 of the bearing 702. The example grooves 706 extend radially from the inner surface 714 of the bearing 702 to the outer surface 716. In addition, the example grooves 706 extend circumferentially along a direction defined by the inner surface 714, such that the grooves 706 surround (e.g., wrap around, track, etc.) an example circumferential surface 718 of the shaft 704.

[0087] exist Figure 7 In the example, the shaft 704 is spaced apart from the bearing 702, thereby defining the example fluid film 720 therebetween. However, during operation, the shaft 704 may move closer to or contact the bearing 702. For example, the shaft 704 may be an impeller shaft of a pump (e.g., Figure 4 The heat transfer bus pump 400 has an impeller shaft 432. In such an example, the shaft 704 can be coupled to an electric motor (e.g., Figure 4 400). In addition, the rotation of shaft 704 can cause shaft 704 to move relative to bearing 702 (e.g., move laterally within bearing 702). Contact or friction between shaft 704 and bearing 702 can increase the local temperature within assembly 700, which in turn can cause NTE material 708 to shrink. Figure 5 and Figure 6 Components 500, Figure 7 The example assembly 700 enables fluid to flow into and out of the groove 706, so that a fluid film 720 is formed between the bearing 702 and the shaft 704. In particular, the shrinkage of the NTE material 708 due to the increase in temperature allows for increased fluid flow. In some examples, the formation of the fluid film 720 between the bearing 702 and the shaft 704 can cause the shaft 704 to return (e.g., move) to a central position within the bearing 702 (e.g., Figure 7 In some examples, bearing 702 can be positioned in an example motor (e.g., Figure 4 Additionally or alternatively, the bearing 702 may be positioned in front of the example motor (e.g., Figure 4 In this way, the example assembly 700 can balance the shaft 704 along the length of the example pump.

[0088] Figure 8-10 An example thrust bearing system 800 according to the teachings disclosed herein is shown. The example thrust bearing system 800 includes an example front thrust bearing (e.g., pad) 802 positioned on the front side of an example thrust disk 804 and an example rear thrust bearing 806 positioned on the rear side of the thrust disk 804. In some examples, the thrust disk 804 is coupled to an impeller shaft of a pump (e.g., the impeller shaft 432 of the heat transfer bus pump 400). In some examples, the thrust bearing system 800 can be positioned in front of the motor in the example pump. Additionally or alternatively, the thrust bearing system 800 can be positioned behind the motor in the example pump. Figure 8-10 The example thrust bearings 802, 806 are similar to Figure 5 and Figure 6804. However, example thrust bearings 802, 806 (e.g., example top foils) may partially surround thrust disk 804. Example front thrust bearing 802 includes example groove 808 having example NTE material 810 disposed therein. Additionally, example rear thrust bearing 806 includes example groove 812 having example NTE material 810 disposed therein.

[0089] For purposes of illustration, the example thrust bearing system 800 is described in conjunction with a pump system in which the thrust disk 804 is coupled to an impeller shaft of the pump (e.g., the impeller shaft 432 of the heat transfer bus pump 400). However, the example thrust bearing system 800 may be described in conjunction with a turbomachine (e.g., an impeller system, a compressor system, a turbine system, a diffuser system, etc.), a gearbox bearing, an electric machine (e.g., an electric motor, a generator, etc.), an electronic device, an electric motor, a dental grinding unit, or any other system. Fig. 9 , the forward displacement of the thrust disk 804 due to the forward thrust of the example impeller shaft can cause the thrust disk 804 to move forward in the thrust bearing system 800. In such an example, the thrust disk 804 moves closer to the front thrust bearing 802, so that the thrust disk 804 contacts the front thrust bearing 802. The contact or friction between the thrust disk 804 and the front thrust bearing 802 can increase the local temperature within the thrust bearing system 800, which in turn can cause the NTE material 810 in the groove 808 of the front thrust bearing 802 to shrink. Similar to Figure 5 and Figure 6 Components 500 and Figure 7 In the example assembly 700, the thrust bearing system 800 enables fluid to flow into and out of the groove 808 so that a fluid film can form between the front thrust bearing 802 and the thrust plate 804. In some examples, the formation of the fluid film between the front thrust bearing 802 and the thrust plate 804 can cause the thrust plate 804 to return (e.g., move) to a center position (e.g., Figure 8 (roughly shown in ).

[0090] Go to Fig.10, the rearward displacement of the thrust disk 804 due to the rearward thrust of the example impeller shaft can cause the thrust disk 804 to move rearward in the thrust bearing system 800. In such an example, the thrust disk 804 moves closer to the rear thrust bearing 806, so that the thrust disk 804 contacts the rear thrust bearing 806. The contact or friction between the thrust disk 804 and the rear thrust bearing 806 can increase the local temperature within the thrust bearing system 800, which in turn can cause the NTE material 810 in the groove 812 of the rear thrust bearing 806 to shrink. This allows fluid to flow into and out of the groove 812, so that a fluid film can be formed between the rear thrust bearing 806 and the thrust disk 804. In some examples, the generation of a fluid film between the rear thrust bearing 806 and the thrust disk 804 can return the thrust disk 804 to a center position (such as Figure 8 ). Figure 8-10 In the example, thrust bearings 802, 806 include example grooves 808, 812 and NTE material 810. However, the example thrust plate 804 may also include example grooves in which NTE material is disposed, as described below in conjunction with Fig.11 Detailed description.

[0091] Fig.11 1 is a cross-section of an example thrust plate 1100 according to the teachings disclosed herein. The example thrust plate 1100 includes an example groove 1102 positioned on an example outer surface 1104 of the thrust plate 1100. In some examples, the outer surface 1104 faces an example bearing 1108 (e.g., Figure 8-10 The example groove 1102 includes an example NTE material 1106 disposed therein. Therefore, contact or friction between the thrust disk 1100 and the bearing 1108 can increase the local temperature between the bearing 1108 and the thrust disk 1100, which in turn can shrink the NTE material 1106 in the groove 1102 of the thrust disk 1100. In this way, the fluid flowing into and out of the groove 1102 of the thrust disk 1100 can generate a fluid film between the thrust disk 1100 and the bearing 1108. In some examples, the thrust disk 1100 can also represent a shaft, wherein the shaft has a groove 1102 positioned on the outer surface 1104 with the NTE material 1106 disposed therein.

[0092] Fig.12 and Fig.13 yes Fig.11Detailed view of a portion of an example thrust disk 1100. An example groove 1102 can be etched into an outer surface 1104, wherein an NTE material 1106 is disposed in the example groove 1102. Additionally, the example groove 1102 can extend from the outer surface 1104 toward an interior portion of the thrust disk 1100. In some examples, the groove 1102 can track (e.g., span, straddle, etc.) a circumferential surface (e.g., outer surface 1104). Additionally or alternatively, the example groove 1102 can extend radially inward from the outer surface 1104. Figure 11-13 As shown, the example grooves 1102 can each have a generally triangular shape, wherein a vertex is formed at the end of each groove. However, the example grooves 1102 can have any shape (e.g., rectangular, oval, etc.). Fig.12 and Fig.13 1104. Example grooves 1102 having similar depths or sizes are shown in FIG. However, the example grooves 1102 can vary in depth or size. Additionally, the example grooves 1102 are shown as being evenly spaced around the outer surface 1104. However, the example grooves 1102 can be randomly spaced relative to the outer surface 1104 or spaced at various distances.

[0093] Fig.14 1 is a cross-section of an example bearing 1400 according to the teachings disclosed herein. The example bearing 1400 includes an example groove 1402 positioned on an example outer surface 1404 of the bearing 1400 and an example groove 1406 positioned on an example inner surface 1408 of the bearing 1400. In addition, the example groove 1402 includes an example NTE material 1410 disposed therein, and the example groove 1406 includes an example NTE material 1412 disposed therein. Thus, the example bearing 1400 can maintain a fluid film between an example shaft positioned within the inner surface 1408 and the example bearing 1400. Additionally or alternatively, the example bearing 1400 can maintain a fluid film between another example bearing or structure positioned adjacent to the example bearing 1400. In this way, the example bearing 1400 can generate a fluid film around the outer surface 1404 and a fluid film around the inner surface 1408 due to the contraction of the NTE materials 1410, 1412 within the corresponding grooves 1402, 1406.

[0094] Fig.15 yes Fig.14 Detailed view of a portion of an example bearing 1400. An example groove 1406 can be etched into an inner surface 1408, wherein an NTE material 1412 is disposed in the example groove 1406. Additionally, an example groove 1402 can be etched into an outer surface 1404, wherein an NTE material 1410 is disposed in the example groove 1402. Fig.15As shown, the example groove 1406 extends toward the example groove 1402. In this example, the example grooves 1402, 1406 present a generally curved or spiral shape. Additionally or alternatively, the example groove 1402 can extend along the outer surface 1404 in a first circumferential direction, and the example groove 1406 can extend along the inner surface 1408 in a second circumferential direction, the second direction being different from the first direction.

[0095] Fig.16 An example bearing system 1600 is shown in which examples disclosed herein may be implemented. The example bearing system 1600 includes an example foil bearing 1602 ("bearing 1602") and an example hole 1604. In some examples, an example shaft is positioned (e.g., placed, inserted, received, etc.) within the hole 1604. Similar to Figure 7 Example of bearing 700, Fig.16 The example bearing 1602 may include an example groove positioned in an example inner surface of the bearing, wherein the example NTE material is disposed in the example groove. In some examples, the bearing 1602 is a top foil of the bearing 1602 such that the top foil faces the shaft. In this way, the example bearing 1602 may maintain a fluid film between the example shaft positioned within the hole 1604 and the bearing 1602. The formation of the fluid film between the bearing 1602 and the shaft may return the shaft to a center position (e.g., an equilibrium position) within the bearing 1602. Additionally or alternatively, the example shaft (positioned within the hole 1604) may include an example groove having the example NTE material disposed therein. Similar to Fig.11 In the example thrust disk 1100, the example shaft may include an example groove positioned on an outer surface of the shaft. In this way, the example shaft can maintain a fluid film between the shaft and the bearing 1602. The shrinkage of the NTE material disposed in the groove of the shaft helps to further locally (e.g., in areas where the shaft and the bearing 1602 are prone to contact / friction due to dynamics or imbalance) in situ balance the shaft. Therefore, both the shaft and the bearing 1602 can include a groove in which the NTE material is disposed. The NTE material associated with both the shaft and the bearing 1602 can shrink to create a fluid film between the shaft and the bearing 1602, thereby balancing the position of the shaft within the bearing 1602.

[0096] Fig.17 is a method for manufacturing the example bearings disclosed herein (e.g., bearings 502, 702, 802, 806, 1400, respectively). Figure 5-10 and Figure 14-15 ) and a flowchart of an example method 1700 for an example thrust plate (e.g., thrust plate 1100). In some examples, at least a portion of the example method 1700 represents example machine-readable instructions that can be executed or instantiated by a processor circuit in communication with a manufacturing device to manufacture an example bearing or an example thrust plate. Additionally or alternatively, Fig.17 The method 1700 may utilize an application specific integrated circuit (ASIC) and / or a field programmable gate array (FPGA) structured so that operations corresponding to the method 1700 are performed by manufacturing equipment.

[0097] Fig.17 The example method 1700 begins at block 1702 where an example bearing is provided. In some examples, at least one of the bearings 502, 702, 802, 806, 1400 is provided. In other examples, a thrust plate 1100 is provided.

[0098] At block 1704, an example groove is formed (e.g., etched) in a surface of an example bearing. For example, example groove 510 is formed in first surface 506 of example bearing 502, example groove 706 is formed in inner surface 714 of example bearing 702, example groove 808 is formed in a surface of example front thrust bearing 802, example groove 812 is formed in a surface of example rear thrust bearing 806, example groove 1406 is formed in inner surface 1408 of bearing 1400, example groove 1402 is formed in outer surface 1404 of bearing 1400, etc. In some examples, groove 1102 is formed in outer surface 1104 of thrust disk 1100. In some examples, grooves 510, 706, 808, 812, 1102, 1406, 1402 ( Figure 5-15 ) is accomplished by nano-grinding or nano-polishing.

[0099] At block 1706, an example NTE material is deposited in the example groove. For example, NTE material 514 is deposited in Figure 5-7 The NTE material 708 is deposited in the groove 510 of Figure 7 The NTE material 810 is deposited in the groove 706 of Figure 8-10 The NTE material 1410 is deposited in the groove 1402, and the NTE material 1412 is deposited in the groove 808, 812. Fig.14 and Fig.15 In some examples, NTE material 1106 is deposited in the groove 1406. Figure 11-13 In some examples, the depth or thickness of the NTE material 514, 708, 810, 1106, 1410 is measured via an ultrasonic meter, an eddy current-based meter, a laser-based meter (e.g., light), a laser-based confocal microscope, or an atomic force microscope (AFM).

[0100] In some examples, assembly 500, assembly 700, thrust bearing system 800, or bearing system 1600 may include a means for supporting. For example, the means for supporting may be composed of Figure 5 and Figure 6 Bearing 502, Figure 7 Bearing 702, Figure 8-10 Bearings 802 and 806, Fig.11 Bearing 1108, Fig.14 and Fig.15 Bearing 1400, Fig.16 The bearing 1602 in the embodiment may be implemented as described above or any other bearing described herein.

[0101] In some examples, Figure 5 and Figure 6 Components 500, Figure 7 Components 700, Figure 8-10 Thrust bearing system 800, Figure 11-13 Example thrust plate 1100, Fig.14 and Fig.15 Example of bearing 1400 or Fig.16 The bearing system 1600 may include a device for contraction. For example, the device for contraction may be composed of Figure 5 and Figure 6 NTE materials in 514, Figure 7 NTE material 708, Figure 8-10 NTE material 810, Figure 11-13 NTE material 1106, Fig.14 The NTE materials 1410, 1412 or any other NTE material described herein may be implemented.

[0102] Disclosed herein are bearings with grooves and methods for producing the same. Disclosed herein are example negative thermal expansion (NTE) materials for use with bearings. The example systems disclosed herein reduce the amount of axial motion experienced by an impeller shaft due to forward and backward thrusts. The example bearing systems disclosed herein can increase the spacing between the impeller shaft and the radial bearing, the spacing between the thrust disc and the corresponding thrust pad, and the like. Therefore, the examples disclosed herein can reduce the frequency or amplitude of the impeller shaft or the portion connected thereto physically contacting other parts and / or the housing of the pump. For example, the examples disclosed herein employ NTE coatings deposited in the grooves to generate gaps between pump components. In addition, the example systems disclosed herein can improve the operating efficiency of the pump by minimizing or otherwise reducing the friction energy losses associated with axial impeller shaft motion. In addition, the example systems disclosed herein can increase the time between maintenance services for repairing and / or replacing components of thrust bearings, motors, pumps, and the like.

[0103] A bearing having a groove and a method for producing the same are disclosed herein. Further aspects of the disclosure are provided by the subject matter of the following clauses:

[0104] An apparatus includes a bearing having a bearing surface with a groove, the bearing being positioned adjacent to a shaft with the groove facing the shaft; and a negative thermal expansion (NTE) material positioned in the groove, the NTE material at least partially filling the groove.

[0105] The apparatus of any preceding clause, wherein the NTE material comprises at least one of zirconium tungstate, zirconium vanadate, or niobium titanium.

[0106] An apparatus as described in any preceding clause, wherein the NTE material is coated on an interior surface of the groove.

[0107] Apparatus according to any preceding clause, wherein the bearing is a radial bearing, the radial bearing surrounding the shaft.

[0108] Apparatus as claimed in any preceding clause, wherein the bearing surface is an inner surface of the radial bearing, wherein the grooves extend radially from the inner surface towards an outer surface of the radial bearing.

[0109] Apparatus according to any preceding clause, wherein the shaft is an impeller shaft of a pump, the impeller shaft being coupled to a rotor of an electric motor, the radial bearing being positioned forwardly of the electric motor or rearwardly of the electric motor.

[0110] An apparatus as in any preceding clause, wherein the NTE material collapses in response to at least one of movement of the impeller shaft relative to the radial bearings, windage heating, or contact with a moving ambient fluid.

[0111] Apparatus according to any preceding clause, wherein the bearing is a thrust bearing, further comprising a thrust plate coupled to the shaft.

[0112] The apparatus of any preceding clause, wherein the thrust bearing is at least one of a bearing top foil facing the thrust disc, a rear thrust bearing positioned at a rear side of the thrust disc, or a front thrust bearing positioned at a front side of the thrust disc.

[0113] Apparatus as claimed in any preceding clause, wherein the bearing surface is an outer surface of the thrust plate, and wherein the outer surface faces the thrust bearing.

[0114] Apparatus according to any preceding clause, wherein the NTE material decreases in size in response to the thrust disc moving relative to the thrust bearing.

[0115] Apparatus according to any preceding clause, wherein the shaft is an impeller shaft of a pump, the impeller shaft being coupled to a rotor of an electric motor, the thrust bearing being positioned forwardly of the electric motor.

[0116] An apparatus as claimed in any preceding clause, wherein the thrust bearing is a first thrust bearing and the recess is a first recess, the apparatus further comprising a second thrust bearing having a second recess, the second thrust bearing being positioned rearwardly of the motor.

[0117] An apparatus according to any preceding clause, wherein the groove is a first groove and the bearing surface is a first bearing surface, the apparatus further comprising a second groove positioned in a second bearing surface, the second bearing surface facing away from the first bearing surface, and wherein the first groove extends along a first circumferential direction and the second groove extends along a second circumferential direction different from the first circumferential direction.

[0118] A device includes: a bearing having a cavity positioned in a surface of the bearing, the surface at least partially surrounding a longitudinal axis of the device; and a negative thermal expansion (NTE) material positioned in the cavity, the NTE material at least partially filling the cavity.

[0119] An apparatus as described in any preceding clause, wherein the NTE material is coated on one or more walls of the cavity.

[0120] Apparatus according to any preceding clause, wherein the bearing is a radial bearing surrounding a shaft aligned with the longitudinal axis.

[0121] Apparatus according to any preceding clause, wherein the NTE material contracts in response to movement of the shaft relative to the radial bearing.

[0122] Apparatus according to any preceding clause, wherein the bearing is a thrust bearing, wherein the thrust bearing is positioned at least partially around a thrust disk.

[0123] The apparatus of any preceding clause, wherein the cavity is a first cavity and the NTE material is a first NTE material, wherein the thrust plate further comprises a second cavity having a second NTE material disposed therein, the second cavity being positioned on an outer surface of the thrust plate, the outer surface of the thrust plate facing the surface of the bearing.

[0124] A device includes: at least one surface having a groove; and a negative thermal expansion (NTE) coating, the NTE coating at least partially covering one or more walls of the groove, the NTE coating being positioned closer to an interior portion of the groove than the at least one surface.

[0125] A method includes providing a bearing; forming a groove in a surface of the bearing; and depositing a negative thermal expansion (NTE) material in the groove.

[0126] An apparatus comprises: a device for supporting, the device for supporting having a bearing surface with a groove, the device for supporting being positioned adjacent to an axis with the groove facing the axis; and a device for shrinking, the device for shrinking being positioned in the groove, the device for shrinking at least partially filling the groove.

[0127] Apparatus according to any preceding clause, wherein said means for contracting is a negative thermal expansion (NTE) material.

[0128] Apparatus according to any preceding clause, wherein the means for shrinking is coated on an interior surface of the recess.

[0129] Apparatus according to any preceding clause, wherein the means for supporting is a radial bearing surrounding the shaft.

[0130] Apparatus as claimed in any preceding clause, wherein the bearing surface is an inner surface of the radial bearing, wherein the grooves extend radially from the inner surface towards an outer surface of the radial bearing.

[0131] Apparatus according to any preceding clause, wherein the shaft is an impeller shaft of a pump, the impeller shaft being coupled to a rotor of an electric motor, the radial bearing being positioned forwardly of the electric motor or rearwardly of the electric motor.

[0132] Apparatus as claimed in any preceding clause, wherein said means for contracting contracts in response to movement of said impeller shaft relative to said radial bearing, windage heating or contact with a moving ambient thermal fluid.

[0133] Apparatus according to any preceding clause, wherein the means for supporting is a thrust bearing, further comprising a thrust plate coupled to the shaft.

[0134] The apparatus of any preceding clause, wherein the thrust bearing is at least one of a bearing top foil facing the thrust disc, a rear thrust bearing positioned at a rear side of the thrust disc, or a front thrust bearing positioned at a front side of the thrust disc.

[0135] Apparatus as claimed in any preceding clause, wherein the bearing surface is an outer surface of the thrust plate, and wherein the outer surface faces the thrust bearing.

[0136] Apparatus according to any preceding clause, wherein the means for contracting decreases in size in response to the thrust disc moving relative to the thrust bearing.

[0137] Apparatus according to any preceding clause, wherein the shaft is an impeller shaft of a pump, the impeller shaft being coupled to a rotor of an electric motor, the thrust bearing being positioned forwardly of the electric motor.

[0138] An apparatus as claimed in any preceding clause, wherein the thrust bearing is a first thrust bearing and the recess is a first recess, the apparatus further comprising a second thrust bearing having a second recess, the second thrust bearing being positioned rearwardly of the motor.

[0139] The following claims are incorporated by reference into this detailed description. Although certain example systems, methods, devices, and articles are disclosed herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all systems, methods, devices, and articles that fully fall within the scope of the patent claims.

Claims

1. A device, characterized in that: include: a bearing having a bearing surface with a groove, the bearing being positioned adjacent to the shaft with the groove facing the shaft; as well as A negative thermal expansion (NTE) material is positioned in the groove, the NTE material at least partially filling the groove.

2. The device according to claim 1, characterized in that in, The NTE material includes at least one of zirconium tungstate, zirconium vanadate or niobium titanium.

3. The device according to claim 1, characterized in that in, The NTE material is coated on one or more walls of the groove.

4. The device according to claim 1, characterized in that in, The bearing is a radial bearing which surrounds the shaft.

5. The device according to claim 4, characterized in that in, The bearing surface is an inner surface of the radial bearing, wherein the groove extends radially from the inner surface toward an outer surface of the radial bearing.

6. The device according to claim 4, characterized in that in, The shaft is an impeller shaft of a pump, the impeller shaft is coupled to a rotor of an electric motor, the radial bearing being positioned in front of the electric motor or behind the electric motor.

7. The device according to claim 6, characterized in that in, The NTE material shrinks in response to at least one of movement of the impeller shaft relative to the radial bearings, windage heating, or contact with a moving ambient thermal fluid.

8. The device according to claim 1, characterized in that in, The bearing is a thrust bearing, further comprising a thrust plate coupled to the shaft.

9. The device according to claim 8, characterized in that in, The thrust bearing is at least one of a bearing top foil facing the thrust plate, a rear thrust bearing positioned at a rear side of the thrust plate, or a front thrust bearing positioned at a front side of the thrust plate.

10. The device according to claim 8, characterized in that in, The bearing surface is an outer surface of the thrust plate, and wherein the outer surface faces the thrust bearing.

Images