A structure for an aviation equipment oil circulation pump with adaptive clearance compensation

Abstract

This invention relates to the field of oil pump technology, specifically to a structure for an aviation equipment oil circulation pump with adaptive clearance compensation. The pump includes a pump body and an impeller. The impeller is mounted in the inner cavity of the pump body via a rotating shaft. An annular flow channel is formed between the outer edge of the impeller and the pump body shell wall. The pump body has an inlet and an outlet communicating with the annular flow channel. A partition is provided on the pump body shell wall, extending into the annular flow channel and dividing it into a low-pressure zone corresponding to the inlet and a high-pressure zone corresponding to the outlet. An actuating core is radially slidably mounted on the partition, with a radial clearance between the end face of the actuating core and the outer edge of the impeller. A pressure balancing passage is provided between the partition and the high-pressure zone of the annular flow channel. This invention has the advantages of automatically compensating for clearance changes, improving volumetric and hydraulic efficiency, and extending equipment service life.

Description

Technical Field

[0001] This invention relates to the field of aviation equipment oil system technology, and more specifically, to an aviation equipment oil circulation pump structure with adaptive clearance compensation. Background Technology

[0002] In the hydraulic systems of aviation equipment, vortex pumps are widely used as key power components in the supply or circulation of aviation kerosene, lubricating oil, and coolant. The core structure of this type of pump includes a pump body, impeller, and an annular flow channel. The pump body casing has a partition to separate the annular flow channel into high-pressure and low-pressure zones, and the impeller is driven by a rotating shaft to achieve oil flow. However, during long-term operation, due to the high-speed flow, high-temperature environment, and chemical corrosiveness of aviation oil, the surface of the partition inevitably suffers continuous erosion, chemical corrosion, and cavitation, leading to a gradual increase in the radial clearance between the partition and the outer edge of the impeller. This increased clearance disrupts the effective seal between the high-pressure and low-pressure zones, causing significant internal fluid leakage and a severe decrease in the pump's volumetric and hydraulic efficiency, specifically manifested as a continuous decline in output flow and insufficient head capacity. Because the clearance change is slow and insidious, conventional maintenance and inspection methods struggle to detect these subtle changes in time. Often, these changes are only noticed by operators when system performance has severely deteriorated or even when the hydraulic system fails, posing a significant threat to the safe operation of aviation equipment. In existing technologies, although there are methods to try to change the clearance by manually adjusting the tightness of bolts, this method relies heavily on the operator's subjective experience and tactile judgment, and lacks objective and precise control standards. If the clearance is set too loosely, the pump's design performance cannot be restored, while if it is set too tight, mechanical friction and wear will be aggravated and may induce impeller seizure, which cannot meet the stringent requirements of aviation equipment for high reliability and long service life.

[0003] To address the aforementioned issues, existing technologies urgently need improvement. Summary of the Invention

[0004] The purpose of this invention is to provide an aviation equipment oil circulation pump structure with adaptive clearance compensation, which has the advantages of reducing internal fluid leakage, maintaining high volumetric efficiency and hydraulic efficiency, and extending pump service life.

[0005] This invention provides a hydraulic circulation pump structure for aviation equipment with adaptive clearance compensation, including a pump body and an impeller. The impeller is mounted in the inner cavity of the pump body via a rotating shaft, and an annular flow channel is formed between the outer edge of the impeller and the pump body shell wall. The pump body has an inlet and an outlet communicating with the annular flow channel. A partition is fixedly provided on the shell wall of the pump body, extending into the interior of the annular flow channel and dividing the annular flow channel into a low-pressure zone corresponding to the inlet and a high-pressure zone corresponding to the outlet. An actuating core is radially slidably mounted on the partition, and an adaptively adjustable radial clearance is formed between the bottom end face of the actuating core and the outer edge of the impeller. A pressure balancing passage is provided inside the partition, communicating with the high-pressure zone of the annular flow channel to introduce high-pressure fluid. A balancing component is provided between the partition and the actuating core, communicating with the pressure balancing passage and receiving high-pressure fluid pressure to drive the actuating core to slide radially to compensate for the radial clearance. An elastic element is provided between the partition and the actuating core, providing a basic preload force for the actuating core, and cooperating with the balancing component to achieve dynamic adaptive compensation of the radial clearance.

[0006] Furthermore, the partition portion has a through cavity, the actuating core is slidably assembled in the through cavity and its lower end extends into the annular flow channel; the elastic element is assembled inside the through cavity and abuts against the partition portion and the actuating core; the balancing assembly includes a hydraulic bladder, which is assembled between the actuating core and the partition portion, the inner cavity of the hydraulic bladder is sealed and connected to the pressure balance passage, and the high-pressure fluid can drive the hydraulic bladder to deform and push the actuating core to slide, thereby achieving adaptive compensation of radial clearance in conjunction with the elastic element.

[0007] Furthermore, the upper end of the actuating core extends through the upper port of the through cavity and is fixedly fitted with a cap. The hydraulic bladder is fitted on the outer side of the upper end of the actuating core, and the upper and lower ends of the hydraulic bladder respectively abut against the lower end face of the cap and the inner step wall of the partition.

[0008] Furthermore, the actuating core is integrally formed with a limiting ring in the middle, and the hydraulic bladder is assembled in the lower cavity of the through cavity. The upper and lower ends of the hydraulic bladder abut against the lower end face of the limiting ring and the inner wall of the partition cavity, respectively.

[0009] Furthermore, the partition section has a through cavity, and the actuating core is slidably assembled in the through cavity with its lower end extending into the annular flow channel; a limiting ring is integrally formed in the middle of the actuating core, and an elastic element is assembled inside the through cavity, with its two ends respectively abutting against the inner wall of the partition section and the upper end face of the limiting ring; the balancing assembly includes an airtight chamber, a piston ring is assembled on the outside of the limiting ring, and a sealing structure is assembled between the actuating core and the lower port of the through cavity; the piston ring, the sealing structure, the outer wall of the actuating core, and the inner wall of the through cavity together enclose the airtight chamber to form an airtight chamber, which is connected to the pressure balance passage, and the high-pressure fluid can form a pneumatic driving force in the airtight chamber to push the actuating core to slide, and cooperate with the elastic element to complete the radial clearance adaptive compensation.

[0010] Furthermore, a valve is installed on the pressure balancing passage, and a synchronous piston is slidably installed in the inner cavity of the valve. The synchronous piston divides the inner cavity of the valve into a first pressure chamber and a second pressure chamber that are independent of each other. The first pressure chamber is connected to a hydraulic bladder or an airtight chamber, and the second pressure chamber is connected to the high-pressure zone of the annular flow channel or the liquid outlet. The synchronous piston is equipped with a return spring to balance the pressure on both sides and buffer pressure fluctuations.

[0011] Furthermore, the pump body shell wall has an installation port, and the partition is radially inserted into the installation port and can be detachably locked and fixed by threads or bolts; a sealing element is installed between the partition and the contact end face of the pump body to seal the assembly gap and prevent media leakage.

[0012] Furthermore, a sliding sealing ring is fitted between the sliding mating surface of the actuating core and the through cavity to seal the sliding gap and prevent the high-pressure fluid from leaking out.

[0013] Furthermore, the annular flow channel is an open flow channel, the impeller is a closed impeller, and the pump body is adapted to transport aviation kerosene, lubricating oil, or cryogenic coolant.

[0014] Furthermore, the elastic element is a compression helical spring, with its upper end abutting against the inner stepped surface of the partition and its lower end abutting against the upper surface of the actuating core or the limiting ring; a spring anti-disengagement ring is installed inside the through cavity to limit the elastic element from shifting or falling off.

[0015] As can be seen from the above, the present invention provides an aviation equipment oil circulation pump structure with adaptive clearance compensation, including a pump body and an impeller. The impeller is installed in the inner cavity of the pump body via a rotating shaft. An annular flow channel is formed between the outer edge of the impeller and the shell wall of the pump body. The pump body is provided with an inlet and an outlet that communicate with the annular flow channel. A partition is fixedly provided on the shell wall of the pump body. The partition extends into the interior of the annular flow channel and divides the annular flow channel into a low-pressure zone corresponding to the inlet and a high-pressure zone corresponding to the outlet. An actuating core is radially slidably mounted on the partition. An adaptively adjustable radial clearance is formed between the bottom end face of the actuating core and the outer edge of the impeller. A pressure balance passage is opened inside the partition, which communicates with the high-pressure zone of the annular flow channel to introduce high-pressure flow. The pump body includes a balancing component between the partition and the actuating core. This component is connected to a pressure balancing passage and can receive high-pressure fluid pressure to drive the actuating core to slide radially to compensate for radial clearance. An elastic element is also provided between the partition and the actuating core. This elastic element provides a basic preload to the actuating core and works in conjunction with the balancing component to achieve dynamic adaptive compensation of the radial clearance. Through the synergistic effect of the partition, the actuating core, the balancing component, and the elastic element, the pump responds in real time to changes in high-pressure fluid pressure and dynamically adjusts the radial clearance to maintain sealing performance. This effectively suppresses internal fluid leakage, significantly improves the pump's operating efficiency and reliability, and offers advantages such as reducing internal fluid leakage, maintaining high volumetric and hydraulic efficiency, and extending service life. Attached Figure Description

[0016] Figure 1 This is a side sectional view of the overall structure of the present invention; Figure 2 This is a partial cross-sectional schematic diagram of the partition portion according to Embodiment 1 of the present invention; Figure 3 This is a partial cross-sectional schematic diagram of the partition portion in Embodiment 2 of the present invention; Figure 4 This is a partial cross-sectional schematic diagram of the partition portion in Embodiment 3 of the present invention; Figure 5 This is a schematic diagram of the valve structure of the present invention.

[0017] In the picture: 1. Pump body; 2. Isolation section; 3. Actuating core; 4. Valve; 100. Annular flow channel; 11. Impeller; 12. Shaft; 13. Inlet; 14. Outlet; 15. Mounting port; 21. Elastic element; 200. Through cavity; 31. Hydraulic bladder; 32. Cap; 33. Limiting ring; 34. Piston ring; 35. Sealing structure; 300. Airtight chamber; 41. Synchronous piston; 42. First pressure chamber; 43. Second pressure chamber. Detailed Implementation

[0018] The technical solution of the present invention will be described below with reference to the accompanying drawings and embodiments.

[0019] In traditional aviation equipment oil circulation pumps, the radial clearance between the partition and the outer edge of the impeller gradually widens during long-term operation due to continuous erosion, chemical corrosion, and cavitation. This increased clearance disrupts the effective seal between the high-pressure and low-pressure areas, leading to significant internal fluid leakage and a severe decrease in the pump's volumetric and hydraulic efficiency, specifically manifested as a continuous reduction in output flow and insufficient head capacity. Current techniques, which attempt to alter the clearance by manually adjusting bolt tightness, heavily rely on the operator's subjective experience and tactile judgment, lacking objective and precise control standards and failing to meet the stringent requirements of aviation equipment for high reliability and long service life.

[0020] Therefore, such as Figure 1-5As shown, this invention proposes a hydraulic oil circulation pump structure for aviation equipment with adaptive clearance compensation. A partition 2 is fixedly installed on the pump body 1 shell wall. An actuating core 3 is radially slidably mounted on the partition 2. The bottom end face of the actuating core 3 forms an adaptively adjustable radial clearance G with the outer edge of the impeller 11. A pressure balancing passage is opened inside the partition 2, connecting to the high-pressure zone of the annular flow channel 100 to introduce fluid pressure. A balancing component is installed between the partition 2 and the actuating core 3, connecting to the pressure balancing passage. The balancing component receives fluid pressure and drives the actuating core 3 to slide radially, achieving radial clearance compensation. An elastic element 21 is also installed between the partition 2 and the actuating core 3. The elastic element 21 provides a basic preload force to the actuating core 3, driving the actuating core 3 towards the impeller 11 to maintain the radial clearance G, thus cooperating with the balancing component to achieve dynamic adaptive compensation of the radial clearance.

[0021] For ease of understanding, the components involved in this invention are described below. The pump body 1 is the main structure of an oil circulation pump, internally forming a cavity space to accommodate an impeller 11 and an annular flow channel 100. The pump body 1 is provided with an inlet 13 and an outlet 14. The impeller 11 is the core rotating component of the pump, assembled in the inner cavity of the pump body 1 via a rotating shaft 12. The other end of the rotating shaft 12 is connected to an external drive device. The rotation of the impeller 11 transfers kinetic energy to the fluid, driving its flow. The annular flow channel 100 is formed between the outer edge of the impeller 11 and the inner wall of the pump body 1. After the fluid is accelerated and pressurized by the impeller 11, it flows within the annular flow channel 100. A partition 2 is fixedly installed on the shell wall of the pump body 1, extending inward into the annular flow channel 100, dividing the annular flow channel 100 into a low-pressure zone and a high-pressure zone, thus realizing the pump's fluid pressurization function. The actuating core 3 is radially slidably mounted on the partition 2. A radial clearance G is formed between the bottom end face of the actuating core 3 and the outer edge of the impeller 11. The radial sliding of the actuating core 3 can change the size of the radial clearance G. The radial clearance G directly affects the pump's sealing performance and operating efficiency. A pressure balancing passage is opened inside the partition 2, introducing the fluid in the high-pressure zone of the annular flow channel 100 into the balancing assembly, serving as the driving source for the sliding of the actuating core 3. An elastic element 21 is arranged between the partition 2 and the actuating core 3, working in conjunction with the balancing assembly to complete the adaptive adjustment of the radial clearance. The balancing assembly, arranged between the partition 2 and the actuating core 3, responds to the fluid pressure, partially offsetting the force of the elastic element 21, causing the actuating core 3 to move radially.

[0022] Example 1

[0023] This embodiment discloses an adaptive clearance compensation structure driven by a hydraulic bladder 31, including a common basic structure such as a pump body 1, impeller 11, annular flow channel 100, partition 2, actuating core 3, and elastic element 21, as well as related drive structures for the hydraulic bladder 31. An installation port 15 is opened in the shell wall of the pump body 1. The partition 2 is radially inserted into the installation port 15. A sealing element is arranged between the partition 2 and the contact end face of the pump body 1 to seal the assembly gap and prevent media leakage. The partition 2 can be integrally cast and welded to the shell wall of the pump body 1, or it can be detachably assembled using bolts and pins, facilitating later maintenance and replacement of parts.

[0024] A through cavity 200 is formed inside the partition section 2. The through cavity 200 is a channel precision-machined within the partition section 2, used to accommodate and guide the actuating core 3 to achieve radial sliding. The actuating core 3 is assembled inside the through cavity 200, with its lower end extending into the annular flow channel 100. The bottom end of the actuating core 3 forms a radial clearance G with the outer edge of the impeller 11. The through cavity 200 can be machined into a cylindrical hole, with a corresponding cylindrical rod body for sliding fit on the actuating core 3. Alternatively, it can be a non-circular cross-section with a guide groove. The actuating core 3 is equipped with a guide protrusion to restrict its circumferential rotation, ensuring stable posture during radial movement and preventing skewing or jamming that could affect the clearance adjustment accuracy.

[0025] A sliding seal ring is fitted onto the sliding mating surface of the actuating core 3 and the through cavity 200. The sliding seal ring seals the assembly gap between the actuating core 3 and the through cavity 200, preventing high-pressure fluid from leaking internally along the sliding gap. This avoids pressure loss within the pressure balance path, ensuring the response sensitivity and gap compensation accuracy of the actuating core 3, while also preventing fluid from flowing from the high-pressure area to the low-pressure area, thus ensuring pump volumetric efficiency. The sliding seal ring can be an elastic seal such as an O-ring, U-ring, or lip seal, relying on its own elasticity and tight fit with the sliding surface to form a dynamic seal. Alternatively, a PTFE sliding ring can be used, which reduces sliding friction resistance while ensuring a good sealing effect.

[0026] The elastic element 21 is arranged inside the through cavity 200, with its two ends abutting against the inner wall of the partition 2 and the actuating core 3, respectively. The elastic element 21 provides a continuous radial preload to the actuating core 3, and the balancing assembly overcomes all or part of the force of the elastic element 21, keeping the radial clearance G at a reasonable value (>0) to prevent the actuating core 3 and the impeller 11 from directly contacting and rubbing together and seizing.

[0027] When the fluid pressure is insufficient or disappears, the elastic element 21 pushes the actuating core 3 to move closer to the impeller 11, reducing the actual radial clearance G and keeping it within the rated range (<0.1). The elastic element 21 can be a compression helical spring, a disc spring assembly, or an elastic rubber polymer elastomer. In this embodiment, the elastic element 21 uses a compression helical spring, with the upper end of the spring abutting against the inner stepped surface of the partition part 2 and the lower end abutting against the actuating core 3 or the upper end surface of the limiting ring 33. A spring anti-disengagement retaining ring is installed inside the through cavity 200. The anti-disengagement retaining ring is a snap ring with an open retaining ring or a welded fixed annular baffle, which limits the axial and radial movement of the elastic element 21, suppresses the spring offset, tilting, and falling off caused by fluid pressure pulsation and overall machine vibration during pump operation, stabilizes the output foundation preload, and ensures the long-term reliable operation of the clearance compensation mechanism.

[0028] In this embodiment, the balancing component uses a hydraulic bladder 31, which is positioned between the actuating core 3 and the partition 2. The inner cavity of the hydraulic bladder 31 is in a sealed connection with the pressure balancing passage. The fluid pressure in the high-pressure zone of the annular flow channel 100 enters the inner cavity of the hydraulic bladder 31 through the pressure balancing passage. The hydraulic bladder 31 can be made of high-strength, media-resistant elastic materials such as fluororubber, nitrile rubber, and polyurethane, possessing high-pressure resistance and anti-aging capabilities. The shape of the hydraulic bladder 31 can be configured as an annular corrugated tube or a flat bladder structure to fit the cavity installation space.

[0029] This embodiment provides two installation arrangements for the hydraulic bladder 31. In the first arrangement, the upper end of the actuating core 3 extends out of the upper port of the through cavity 200. A cap 32 is fixedly mounted on the upper end of the actuating core 3. The cap 32 can be threaded and welded to the top of the actuating core 3 with an interference fit pin, or it can be integrally machined with the actuating core 3. The hydraulic bladder 31 is fitted onto the outer side of the upper end of the actuating core 3, with the upper end of the hydraulic bladder 31 abutting against the lower end face of the cap 32, and the lower end of the hydraulic bladder 31 abutting against the inner stepped wall of the partition part 2. The upper and lower ends of the hydraulic bladder 31 are axially limited. After fluid pressure fills the hydraulic bladder 31, the hydraulic bladder 31 expands, generating axial thrust. This thrust is transmitted to the actuating core 3 through the cap 32, offsetting the basic preload of the elastic element 21 and maintaining the radial clearance G within a reasonable range, ensuring the pump's output efficiency. A gasket sealing ring can be added at the abutment position to compensate for machining tolerances and prevent media leakage from the mating position. In the second arrangement, a limiting ring 33 is integrally formed in the middle of the actuating core 3. The limiting ring 33 is a radially outward protruding ring structure of the actuating core 3. The integral forming ensures the coaxiality of the limiting ring 33 and the actuating core 3, avoiding deflection caused by assembly deviations. The hydraulic bladder 31 is arranged in the lower cavity of the through cavity 200. The upper end of the hydraulic bladder 31 abuts against the lower end face of the limiting ring 33, and the lower end of the hydraulic bladder 31 abuts against the inner wall of the partition 2 cavity. Fluid pressure enters the hydraulic bladder 31, and the expansion of the hydraulic bladder 31 generates a radial force applied to the limiting ring 33, counteracting the basic preload of the elastic element 21, keeping the radial clearance G within a reasonable range, and ensuring the pump's output efficiency. The bidirectional abutment constrains the working position of the hydraulic bladder 31, preventing the hydraulic bladder 31 from shifting and overturning when compressed, ensuring stable thrust output.

[0030] When the fluid pressure is insufficient, the internal sealing of the pump body 1 is insufficient, affecting the output performance. The internal pressure of the hydraulic bladder 31 drops, and the radial force generated by the expansion displacement is less than the basic preload of the elastic element 21. The elastic element 21 drives the action core 3 to move towards the impeller 11, so that the radial clearance G is reduced and maintained within a reasonable range, ensuring the output performance of the pump.

[0031] In this embodiment, a valve 4 is assembled in the pressure balance passage. A synchronous piston 41 is slidably installed inside the valve 4, dividing the inner cavity of the valve 4 into two independent pressure chambers: a first pressure chamber 42 and a second pressure chamber 43. The second pressure chamber 43 is connected to the high-pressure zone of the annular flow channel 100 or the pump outlet 14, directly receiving high-pressure fluid with pressure pulsation. The first pressure chamber 42 is connected to the inner cavity of the hydraulic bladder 31, outputting buffered and stabilized fluid pressure to the hydraulic bladder 31. The synchronous piston 41 is equipped with a return spring, which can be a helical spring, disc spring, or wave spring. When the fluid pressure inside the annular flow channel 100 fluctuates, the synchronous piston 41 reciprocates under the combined action of the pressure difference on both sides and the return spring, filtering and buffering the pressure fluctuations, eliminating pressure shocks, and outputting stable drive pressure to the hydraulic bladder 31. This prevents the actuating core 3 from frequently oscillating with pressure, ensuring smooth and stable radial clearance adjustment, improving the reliability of the mechanism, and extending the service life of components.

[0032] In this embodiment, the pump body 1 is compatible with media including aviation kerosene, lubricating oil, and cryogenic coolant. The annular flow channel 100 is configured as an open flow channel, and the impeller 11 is a closed impeller. The open flow channel is not completely closed radially, allowing for partial fluid exchange, which facilitates the formation of vortex flow, reduces internal flow resistance, and improves the energy exchange efficiency of the impeller 11. The closed impeller blades are equipped with front and rear cover plates on both sides, and the blades are sealed by the cover plates, allowing the fluid to flow only along the blade flow channel, reducing internal backflow leakage and improving the pump's head output capacity. The flow-through components such as the pump body 1, impeller 11, and partition 2 are made of stainless steel, titanium alloy, and aviation composite materials, suitable for the corrosive environment of aviation media. The non-metallic parts such as the hydraulic bladder 31, sliding seal ring, and elastic element 21 are made of special rubber polymer materials compatible with aviation kerosene, lubricating oil, and cryogenic coolant, maintaining elasticity and sealing performance over a wide temperature range.

[0033] In this embodiment, after the pump starts working, the impeller 11 rotates, and the medium, after being pressurized, enters the annular flow channel 100. A portion of the high-pressure medium enters the second pressure chamber 43 of the valve 4 through the pressure balance passage. After being stabilized by the buffer structure composed of the synchronous piston 41 and the return spring, it is sent into the hydraulic bladder 31. The hydraulic bladder 31 expands under pressure, generating thrust that partially offsets the preload of the elastic element 21, maintaining the radial clearance G within a reasonable range (0mm < G < 0.1mm). The higher the pump output pressure, the greater the internal pressure of the hydraulic bladder 31, which can completely overcome the force of the elastic element 21 and stabilize the radial clearance G. When the pump output pressure decreases, the internal pressure of the hydraulic bladder 31 decreases accordingly. The elastic element 21 pushes the actuating core 3 towards the impeller 11, reducing the radial clearance G and maintaining the pump's normal output performance. When the pressure pulsates violently, the synchronous piston 41 inside the valve 4 absorbs the pressure fluctuations, keeping the driving pressure stable, and the actuating core 3 does not vibrate frequently. The partition 2 is quickly disassembled and assembled through the pump body 1 mounting port 15, and the seal prevents the medium from leaking out. The sliding seal ring suppresses internal leakage of the driving medium, and the spring anti-disengagement ring ensures the stability of the elastic element 21. This embodiment relies on the pump's own high-pressure medium to achieve self-compensation of the gap, without the need for an external power source. The radial gap G is dynamically adjusted according to the actual output pressure of the pump, taking into account both the sealing capability under high-pressure conditions and the anti-scratching requirements under low-pressure conditions.

[0034] Example 2

[0035] The difference between this embodiment and Embodiment 1 is that the balancing component is replaced with a piston structure of the airtight chamber 300, and the hydraulic bladder 31 is eliminated, solving the problems of aging and failure of the rubber bladder under long-term high-pressure conditions and insufficient pressure displacement control accuracy under complex conditions. A through cavity 200 is opened in the partition part 2, and the actuating core 3 is slidably assembled in the through cavity 200. A limiting ring 33 is integrally formed in the middle of the actuating core 3, and a piston ring 34 is assembled on the outside of the limiting ring 33, forming a sliding seal with the inner wall of the through cavity 200. A sealing structure 35 is assembled between the actuating core 3 and the lower port of the through cavity 200. The sealing structure 35 can be a combination of O-ring and lip seal. The piston ring 34 on the outside of the limiting ring 33, the lower port sealing structure 35, the outer wall of the actuating core 3, and the inner wall of the through cavity 200 together form a sealed airtight chamber 300. The airtight chamber 300 is connected to the first pressure chamber 42 of the valve component 4 through a pressure balancing passage, and the high-pressure medium after buffering and stabilization is introduced into the airtight chamber 300. The high-pressure medium forms a pneumatic driving force inside the airtight chamber 300. The pressure acts on the end face of the limiting ring 33, pushing the entire actuating core 3 to slide radially away from the impeller 11, overcoming the force of the elastic element 21 to maintain the stability of the radial gap G between the bottom end of the actuating core 3 and the outer edge of the impeller 11.

[0036] The piston ring 34 is made of wear-resistant and corrosion-resistant polytetrafluoroethylene high-performance polymer or special rubber, suitable for aviation media environments. Single or multiple piston rings 34 can be installed to improve the sealing performance of the airtight chamber 300 and reduce media leakage. The lower port sealing structure 35 isolates the airtight chamber 300 from the lower annular flow channel 100, preventing high-pressure media inside the airtight chamber 300 from directly entering the low-pressure side of the annular flow channel 100, thus maintaining stable internal pressure within the airtight chamber 300.

[0037] The elastic element 21 is arranged inside the through cavity 200. Both ends of the elastic element 21 abut against the inner step of the partition 2 and the upper surface of the limiting ring 33, respectively. The elastic element 21 is a compression helical spring. A spring anti-disengagement retaining ring is installed inside the through cavity 200 to prevent the spring from shifting or falling off. When the medium pressure inside the airtight chamber 300 pushes the limiting ring 33 upwards, it needs to overcome the preload of the elastic element 21. When the pressure in the airtight chamber 300 decreases, the elastic element 21 pushes the limiting ring 33, causing the core 3 to move closer to the impeller 11, reducing the radial clearance G and enhancing the pump's internal sealing to improve its output performance.

[0038] The pressure balance passage is still equipped with a valve 4 with a synchronous piston 41 at the front end. The second pressure chamber 43 is connected to the medium in the high pressure zone of the annular flow channel 100. The first pressure chamber 42 is connected to the airtight chamber 300 to filter and buffer the medium pressure entering the airtight chamber 300, so that the pressure in the airtight chamber 300 is synchronized with the pressure in the high pressure zone in real time, and the fluid pressure pulsation impact is eliminated. This ensures that the driving pressure of the airtight chamber 300 is stable, avoids high-frequency reciprocating oscillation of the actuator 3, and improves the piston sliding stability and service life.

[0039] This embodiment also employs an open annular flow channel 100 paired with a closed impeller, making the pump suitable for conveying aviation kerosene, lubricating oil, and cryogenic coolant. The pump body 1, partition section 2, and impeller 11 are made of aviation corrosion-resistant alloy, while the piston ring 34, sealing structure 35, and elastic element 21 are made of temperature-resistant and aging-resistant materials suitable for aviation media. The partition section 2 adopts a radial insertion mounting port 15 structure, combined with end face seals, facilitating easy disassembly and maintenance. The sliding sealing ring is assembled between the actuating core 3 and the sliding pair of the through cavity 200, reducing leakage of the medium in the airtight chamber 300 along the sliding pair gap and ensuring stable driving pressure.

[0040] In this embodiment, during operation, the pump starts, and the impeller 11 rotates to increase pressure. High-pressure medium is introduced into the second pressure chamber 43 of the valve 4 through the annular flow channel 100. After being stabilized by the synchronous piston 41 and the reset spring, the synchronous piston 41 compresses the first pressure chamber 42, causing the pressure to be introduced into the airtight chamber 300. The pressure in the airtight chamber 300 increases, acting on the lower end face of the limit ring 33, overcoming the preload of the upper elastic element 21 to maintain the stability of the radial clearance G, and suppressing leakage of the medium under high pressure. When the pump output pressure decreases, the pressure in the airtight chamber 300 decreases accordingly. The elastic element 21 pushes the limit ring 33, causing the actuating core 3 to move forward, compensating for the loss of radial clearance G, maintaining the radial clearance G within a reasonable value, improving the pump's internal sealing to restore pump performance. When the fluid experiences pressure pulsation, the synchronous piston 41 inside the valve 4 dynamically adjusts, preventing drastic pressure fluctuations within the airtight chamber 300, and maintaining the stable position of the actuating core 3. The airtight chamber 300 employs a piston ring 34 mechanical seal structure, which does not rely on rubber bladder deformation, avoiding the risk of failure due to aging of the hydraulic bladder 31. It offers better pressure and displacement linearity and stronger adaptability to complex aerospace conditions. The partition section 2 can be completely disassembled for inspection and replacement of the piston ring 34 sealing structure 35. The sliding seal ring reduces internal leakage of the medium, and the spring anti-disengagement ring ensures the stability of the elastic element 21's working position. The entire mechanism relies on the pump's own fluid pressure to achieve adaptive clearance adjustment, eliminating the need for an additional external drive mechanism.

[0041] The above description is only a preferred embodiment of the present invention. Therefore, all equivalent changes or modifications made to the structure, features and principles described in the claims of this patent application are included in the scope of this patent application.

Claims

1. A hydraulic oil circulation pump structure for aviation equipment with adaptive clearance compensation, comprising a pump body (1) and an impeller (11), wherein the impeller (11) is mounted in the inner cavity of the pump body (1) via a rotating shaft (12), and an annular flow channel (100) is formed between the outer edge of the impeller (11) and the shell wall of the pump body (1), and the pump body (1) is provided with an inlet (13) and an outlet (14) communicating with the annular flow channel (100), characterized in that: The pump body (1) is fixedly provided with a partition (2) on the shell wall. The partition (2) extends into the annular flow channel (100) and divides the annular flow channel (100) into a low-pressure zone corresponding to the liquid inlet (13) and a high-pressure zone corresponding to the liquid outlet (14). An actuating core (3) is radially slidably mounted on the partition (2). An adaptively adjustable radial clearance (G) is formed between the bottom end face of the actuating core (3) and the outer edge of the impeller (11). A pressure balancing passage is provided inside the partition (2). The pressure balancing passage is connected to the high-pressure area of ​​the annular flow channel (100) to introduce high-pressure fluid. A balancing component is provided between the partition (2) and the actuating core (3). The balancing component is a hydraulic bladder (31) or an airtight chamber (300). The balancing component is connected to the pressure balancing passage and can receive high-pressure fluid pressure to drive the actuating core (3) to slide radially to compensate for the radial clearance (G). An elastic element (21) is provided between the partition (2) and the actuating core (3). The elastic element (21) provides a reset preload for the actuating core (3) and works with the balancing assembly to achieve dynamic adaptive compensation of the radial clearance (G).

2. The structure of the aviation equipment oil circulation pump with adaptive clearance compensation according to claim 1, characterized in that: The partition (2) has a through cavity (200), the actuating core (3) is slidably assembled in the through cavity (200) and its lower end extends into the annular flow channel (100); the elastic element (21) is assembled inside the through cavity (200) and abuts between the partition (2) and the actuating core (3); the balancing component is a hydraulic bladder (31), the hydraulic bladder (31) is assembled between the actuating core (3) and the partition (2), the inner cavity of the hydraulic bladder (31) is sealed and connected to the pressure balance passage, the high pressure fluid can drive the hydraulic bladder (31) to deform and push the actuating core (3) to slide, and cooperate with the elastic element (21) to realize the adaptive compensation of radial clearance (G).

3. The structure of the aviation equipment oil circulation pump with adaptive clearance compensation according to claim 2, characterized in that: The upper end of the actuating core (3) extends through the upper port of the through cavity (200) and is fixedly fitted with a cap (32). The hydraulic bladder (31) is fitted on the outer side of the upper end of the actuating core (3). The upper and lower ends of the hydraulic bladder (31) respectively abut against the lower end face of the cap (32) and the inner step wall of the partition part (2).

4. The structure of the aviation equipment oil circulation pump with adaptive clearance compensation according to claim 2, characterized in that: The action core (3) is integrally formed with a limiting ring (33) in the middle. The hydraulic bladder (31) is assembled in the lower cavity of the through cavity (200). The upper and lower ends of the hydraulic bladder (31) respectively abut against the lower end face of the limiting ring (33) and the inner wall of the cavity of the partition part (2).

5. The structure of the aviation equipment oil circulation pump with adaptive clearance compensation according to claim 1, characterized in that: The partition (2) has a through cavity (200), and the actuating core (3) is slidably assembled in the through cavity (200) with its lower end extending into the annular flow channel (100); the actuating core (3) has an integrally formed limiting ring (33) in the middle, and the elastic element (21) is assembled inside the through cavity (200), with its two ends respectively abutting against the inner wall of the partition (2) and the upper end face of the limiting ring (33); the balancing assembly is an airtight chamber (300), and a piston ring (3) is assembled on the outside of the limiting ring (33). 4) A sealing structure (35) is assembled between the actuating core (3) and the lower port of the through cavity (200); the piston ring (34), the sealing structure (35), the outer wall of the actuating core (3) and the inner wall of the through cavity (200) together form an airtight chamber (300). The airtight chamber (300) is connected to the pressure balance passage. High pressure fluid can form a pneumatic driving force in the airtight chamber (300) to push the actuating core (3) to slide, and cooperate with the elastic element (21) to complete the adaptive compensation of radial clearance (G).

6. The structure of the aviation equipment oil circulation pump with adaptive clearance compensation according to claim 3, 4 or 5, characterized in that: A valve (4) is installed on the pressure balancing passage. A synchronous piston (41) is slidably installed in the inner cavity of the valve (4). The synchronous piston (41) divides the inner cavity of the valve (4) into a first pressure chamber (42) and a second pressure chamber (43) that are independent of each other. The first pressure chamber (42) is connected to a hydraulic bladder (31) or an airtight chamber (300). The second pressure chamber (43) is connected to the high-pressure zone of the annular flow channel (100) or the outlet (14). The synchronous piston (41) is equipped with a reset spring to balance the pressure on both sides and buffer pressure fluctuations.

7. The structure of the aviation equipment oil circulation pump with adaptive clearance compensation according to claim 1, characterized in that: The pump body (1) has an installation port (15) on its shell wall. The partition part (2) is radially inserted into the installation port (15) and is detachably locked and fixed by threads or bolts. A sealing element is installed between the partition part (2) and the contact end face of the pump body (1) to seal the assembly gap and prevent media leakage.

8. The structure of the aviation equipment oil circulation pump with adaptive clearance compensation according to claim 2 or 5, characterized in that: A sliding sealing ring is fitted between the sliding mating surface of the actuating core (3) and the through cavity (200) to seal the sliding gap and prevent the high-pressure fluid from leaking out.

9. The structure of the aviation equipment oil circulation pump with adaptive clearance compensation according to claim 1, characterized in that: The annular flow channel (100) is an open flow channel, the impeller (11) is a closed impeller, and the pump body (1) is adapted to transport aviation kerosene, lubricating oil or cryogenic coolant.

10. The structure of the aviation equipment oil circulation pump with adaptive clearance compensation according to claim 2 or 5, characterized in that: The elastic element (21) is a compression helical spring. The upper end of the elastic element (21) abuts against the inner step surface of the partition part (2), and the lower end abuts against the upper surface of the actuating core (3) or the limiting ring (33). The through cavity (200) is equipped with a spring anti-dislodgement ring to limit the elastic element (21) from shifting or falling off.

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