Dual three way valve for dual mode fuel oil system of more electric aircraft engine

Abstract

The utility model provides a kind of duplex three-way valve for multi-electric aero-engine dual-mode fuel oil system. Including including shell, electromagnet, first valve core, second valve core and connecting rod, second outlet, pump outlet, first outlet, second inlet, pump inlet and first inlet are sequentially provided with in the shell, inside is equipped with second valve core, connecting rod and first valve core in sequence, the shell one end is closed, another end is equipped with electromagnet and is connected first valve core, connecting rod and shell sliding link, and the shell is divided into two areas, one is second outlet and pump outlet communication, while second inlet and pump inlet communication, another is first outlet and pump outlet communication, while first inlet and pump inlet communication. The duplex three-way valve for multi-electric aero-engine dual-mode fuel oil system solves the existing aero-engine range limited, and maintenance difficulty and maintenance cost higher problem.

Description

Technical Field

[0001] This utility model relates to the field of valve bodies, specifically to a dual three-way valve for a dual-mode combustion lubricating oil system in a multi-electric aero-engine. Background Technology

[0002] A certain cruise missile uses an aero-engine to provide thrust for cruise. This aero-engine employs a closed-loop lubrication system, requiring the transport of 20 liters of Pegasus II aviation lubricating oil and a bulky oil cooler, significantly increasing the design difficulty given the stringent space and weight management requirements. Especially after the warhead and seeker were determined, the fuel tank capacity was also constrained, affecting the missile's range. The overall design considered a fuel-oil mixture combustion scheme (fuel: lubricating oil = 95%:5% to 98%:2%). Performance calculations revealed an increased missile range because the lubricating oil also participates in combustion and is almost completely consumed. The disadvantage is that routine maintenance requires mixing the fuel-oil mixture, resulting in high lubricating oil consumption. Furthermore, because the high-flow-rate fuel pump cannot simultaneously meet the requirements of low-flow-rate, high-pressure ignition fuel, insufficient lubricating oil pressure exists at low speeds, leading to a high rate of dry friction damage to bearings and poor starting reliability. There is also the problem of a small amount of residual fuel and lubricating oil not being fully combusted, resulting in range loss. To increase range while reducing maintenance difficulty and costs, a combination of two approaches is being considered: initially, fuel and lubricating oil operate independently, and later they are mixed for combustion. This requires a dedicated valve body that allows the existing lubricating oil pump to simultaneously perform multiple functions, including pre-lubrication pump, atomizing ignition fuel pump, lubrication pump, return oil pump, and mixing fuel pump. Utility Model Content

[0003] To address the limitations of existing aero-engine range, as well as the high difficulty and cost of maintenance, this invention provides a dual three-way valve for a dual-mode fuel-lubricating oil system in multi-electric aero-engines, which enables a single pump to perform multiple functions to solve the aforementioned problems.

[0004] A dual-way three-position valve for a dual-mode fuel and lubricating oil system in a multi-electric aero-engine includes a housing, an electromagnet, a first valve core, a second valve core, and a connecting rod. A second outlet, a pump outlet, a first outlet, a second inlet, a pump inlet, and a first inlet are sequentially arranged through the housing. The second valve core, the connecting rod, and the first valve core are sequentially arranged inside the housing. One end of the housing is closed, and the other end has the electromagnet connected to the first valve core. The connecting rod is slidably connected to the housing and divides the housing into two zones. One zone connects the second outlet, the pump outlet, and the first outlet; the other zone connects the second inlet, the pump inlet, and the first inlet. One connection connects the second outlet and the pump outlet, and simultaneously the second inlet and the pump inlet; the other connection connects the first outlet and the pump outlet, and simultaneously the first inlet and the pump inlet.

[0005] In a preferred embodiment of the dual three-way valve for a dual-mode fuel lubricating oil system of a multi-electric aero-engine provided by this utility model, a second outlet, a first outlet, a second inlet and a first inlet are sequentially provided through one side of the housing; on the other side opposite to the aforementioned four openings, a pump outlet is provided through the valve at the position between the second outlet and the first outlet, and a pump inlet is provided through the valve at the position between the first inlet and the second inlet.

[0006] In a preferred embodiment of the dual-way three-position valve for a dual-mode fuel-lubricating oil system of a multi-electric aero-engine provided by this utility model, a valve sleeve is provided inside the housing. The valve sleeve has annular connecting cavities at the positions of the second outlet, pump outlet, first outlet, pump inlet, first inlet, and second inlet, respectively. Each connecting cavity has an opening leading to the inside of the valve sleeve. The valve sleeve contains, in sequence, the second valve core, the connecting rod, and the first valve core. One end of the valve sleeve is closed, and the other end is open, allowing the electromagnet to connect to the first valve core. An intermediate valve sleeve is provided inside the valve sleeve, and the connecting rod slidably connects to the intermediate valve sleeve, dividing the inside of the valve sleeve into two zones.

[0007] In a preferred embodiment of the dual-way three-way valve for a dual-mode fuel-lubricating oil system of a multi-electric aero-engine provided by this utility model, the second valve core includes a valve seat, a second spring, a second push rod, and a sealing unit. The valve seat is disposed within the valve sleeve, with a second valve cavity communicating with the pump outlet at the middle position, and channels at both ends communicating with the second outlet and the first outlet to the two ends of the second valve cavity. The middle section of the sealing unit passes through the second valve cavity, and both ends are located within the two channels. One end of the sealing unit abuts against the closed end of the valve sleeve via the second push rod and the second spring, and the other end abuts against the connecting rod. The sealing unit includes a first push rod passing through the valve cavity and ceramic sealing balls located outside the two ends of the valve cavity. The ceramic sealing balls can abut against the openings at both ends of the valve cavity to close the valve cavity.

[0008] In a preferred embodiment of the dual three-way valve for a dual-mode fuel lubrication system of a multi-electric aero-engine provided by this utility model, one end of the connecting rod passes through the valve seat and abuts against the sealing unit, while simultaneously abutting against the valve seat via a first spring. The middle section slides into contact with the intermediate valve sleeve, and the other end abuts against the first valve core via a connecting rod spring.

[0009] In a preferred embodiment of the dual three-way valve for a dual-mode fuel lubrication system of a multi-electric aero-engine provided by this utility model, the two ends of the first valve core are slidably connected to the valve sleeve, and the outer side of the middle section is provided with an annular first valve cavity. The first valve cavity connects the second inlet to the pump inlet, or connects the first inlet to the pump inlet.

[0010] Compared with existing technologies, the dual three-way valve for dual-mode fuel lubrication systems in multi-electric aircraft engines provided by this utility model has the following advantages: 1. The dual three-way valve provided by this utility model enables phased combustion control, that is, initially, fuel and lubricating oil work independently, and later, fuel and lubricating oil are mixed for combustion. This significantly reduces the weight of the fuel system, not only improving the thrust-to-weight ratio but also significantly reducing design complexity. Simultaneously, it ensures complete combustion of all fuel, maintaining engine operation and greatly extending loiter time, resulting in significantly improved energy efficiency and extended range.

[0011] 2. The dual three-way valve in this utility model is designed with a controllable leakage mode at the low-pressure end connecting the fuel tank and the lubricating oil tank. Without affecting the function, the structure of the dual valve is simplified, the weight is significantly reduced, and the thrust-to-weight ratio is further improved. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of a double three-way valve used in the dual-mode fuel lubrication system of multi-electric aircraft engines. Figure 2 yes Figure 1 A magnified view of the second valve core location.

[0013] The following are the labels in the diagram: housing 1, lubricating oil outlet 11, fuel outlet 12, lubricating oil inlet 13, fuel inlet 14, pump outlet 15, pump inlet 16, electromagnet 2, valve sleeve 3, intermediate valve sleeve 31, second valve core 4, valve seat 41, second spring 42, second push rod 43, first spring 44, first push rod 45, ceramic sealing ball 46, second valve chamber 47, lubricating oil passage 48, fuel passage 49, first valve core 5, first valve chamber 51, connecting rod 6, connecting rod spring 61. Detailed Implementation

[0014] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0015] Please also refer to Figure 1 and Figure 2 The figures provided are a schematic diagram of the double three-way valve for a dual-mode fuel-lubricating oil system in a multi-electric aero-engine, and a partially enlarged view of the second valve core position. It should be noted that the provided figures are for illustrative purposes only and do not represent the preferred embodiment based on this invention.

[0016] The dual three-way valve for the dual-mode fuel lubrication system of multi-electric aircraft engines includes a housing 1, an electromagnet 2, a valve sleeve 3, a second valve core 4, a first valve core 5, and a connecting rod 6.

[0017] The housing 1 is a cylindrical housing, with an end cap on the left end for closure and an electromagnet 2 on the right end. The upper side has four openings, from left to right: an oil outlet 11, a fuel outlet 12, an oil inlet 13, and a fuel inlet 14. The lower side has two openings, located between the oil outlet 11 and fuel outlet 12, and between the oil inlet 13 and fuel inlet 14, respectively, with a pump outlet 15 and a pump inlet 16 installed from left to right. A valve sleeve 3 is located inside.

[0018] The valve sleeve 3 is also a cylindrical structure, with an end cap on the left end for closure and a threaded connection to the electromagnet 2 on the right end. Multiple raised rings are provided on the outer side, and a sealing ring is provided on each raised ring, creating annular connecting cavities at the six openings of the housing 1. Each connecting cavity has an opening that penetrates into the valve sleeve 3. To avoid visual clutter, these openings are not shown in the attached drawings, but this does not affect those skilled in the art's understanding and implementation of this solution.

[0019] An intermediate valve sleeve 31 is further installed in the middle position of the valve sleeve 3 via threads. The intermediate valve sleeve 31 is also a cylindrical structure, and a sealing ring is provided between it and the valve sleeve 3. The connecting rod 6 passes through the intermediate valve sleeve 31 and slides with it in a clearance fit. The intermediate valve sleeve 31 and the connecting rod 6 work together to divide the internal space of the valve sleeve 3 into two regions, left and right. Without considering the valve core, the left region is connected to the lubricating oil outlet 11, the fuel outlet 12, and the pump outlet 15, while the right region is connected to the lubricating oil inlet 13, the fuel inlet 14, and the pump inlet 16.

[0020] The left side region is provided with a second valve core 4, which includes a valve seat 41, a second spring 42, a second push rod 43, a first spring 44, a first push rod 45, and a ceramic sealing ball 46.

[0021] The valve seat 41 is also a cylindrical structure. Its left end is sealed against the end cap of the valve sleeve 3, and its right end has an opening for the connecting rod 6 to be inserted, and a first spring 44 is provided to abut against it.

[0022] The valve seat 41 has a second valve chamber 47 in the middle position that communicates with the pump outlet 15. At both ends, there are channels that connect the lubricating oil outlet 11 and the fuel outlet 12 to the two ends of the second valve chamber 47, which are respectively referred to as the lubricating oil channel 48 and the fuel channel 49.

[0023] The first push rod 45 is movably positioned within the second valve chamber 47, and two ceramic sealing balls 46 are movably positioned within the oil passage 48 and the fuel passage 49. The ceramic sealing balls 46 in the oil passage 48 abut against the end cap of the valve sleeve 3 via the second push rod 43 and the second spring 42. The ceramic sealing balls 46 in the fuel passage 49 abut against the connecting rod 6.

[0024] Under the aforementioned mechanism, if connecting rod 6 moves to the left, it sequentially pushes the ceramic sealing ball 46 located in fuel passage 49, the first push rod 45, the ceramic sealing ball 46 located in lubricating oil passage 48, and the second push rod 43 to the left, simultaneously compressing the second spring 42 and the first spring 44. This causes the ceramic sealing ball 46 located in fuel passage 49 to close the right end of the second valve chamber 47, while the ceramic sealing ball 46 located in lubricating oil passage 48 opens the right end of the second valve chamber 47. Ultimately, this achieves closure from pump outlet 15 to fuel outlet 12 and connection from pump outlet 15 to lubricating oil outlet 11.

[0025] Conversely, if the second spring 42 and the first spring 44 work together to push the second push rod 43, the ceramic sealing ball 46 located in the lubricating oil passage 48, the first push rod 45, the ceramic sealing ball 46 located in the fuel passage 49, and the connecting rod 6 to the right, then the pump outlet 15 to the fuel outlet 12 will be connected, and the pump outlet 15 to the lubricating oil outlet 11 will be closed.

[0026] A first valve core 5 is provided in the right-side area. The first valve core 5 is a rod-shaped structure, with both ends slidingly connected to the valve sleeve 3 through clearance fit, and a ring-shaped first valve cavity 51 is provided in the middle area. The left end of the first valve core 5 abuts against the connecting rod 6, and the right end is connected to the electromagnet 2.

[0027] Electromagnet 2 drives the first valve core 5 to move left and right. When it moves to the left, the opening of the valve sleeve 3 corresponding to the fuel inlet 14 is blocked, and the lubricating oil inlet 13 and the pump inlet 16 are connected. When it moves to the right, the opening of the valve sleeve 3 corresponding to the lubricating oil inlet 13 is blocked, and the fuel inlet 14 and the pump inlet 16 are connected.

[0028] When the first valve core 5 moves to the left, it sequentially pushes the connecting rod 6 and the ceramic sealing ball 46 and the first push rod 45, which are located in the fuel passage 49 as described above. When it moves to the right, the pressure applied by the connecting rod 6 disappears, and under the combined action of the second spring 42 and the first spring 44, the second push rod 43 and the ceramic sealing ball 46, which are located in the lubricating oil passage 48, are sequentially pushed to the right.

[0029] That is, the left-hand route is connected to the lubricating oil inlet 13, the oil pump, and the lubricating oil outlet 11, and the right-hand route is connected to the fuel inlet 14, the oil pump, and the fuel outlet 12.

[0030] The connecting rod 6 gradually thickens from left to right. The thinnest section at the left end slides into the valve seat 41, the second thinnest section slides into the intermediate valve sleeve 31, and the thickest section at the right end abuts against the first valve core 5. The right end face is concave, and a connecting rod spring 61 is provided therein to abut against the first valve core 5. This is used to buffer the resistance difference between the first valve core 5 and the second valve core 4, preventing pulling.

[0031] In operation, the oil pump is connected between pump outlet 15 and pump inlet 16. When electromagnet 2 drives the first valve core 5 to move to the left, the route from lubricating oil inlet 13, oil pump, and lubricating oil outlet 11 is connected, enabling the oil pump to perform functions such as pre-lubrication pump, lubrication pump, and return oil pump. When electromagnet 2 drives the first valve core 5 to move to the right, the route from fuel inlet 14, oil pump, and fuel outlet 12 is connected, enabling the oil pump to perform functions such as ignition fuel pump and auxiliary fuel pump.

[0032] When the electromagnet 2 drives the first valve core 5 to move back and forth continuously, the lubricating oil from the lubricating oil inlet 13 and the fuel from the fuel inlet 14 can be mixed evenly in the first valve chamber 51 to form a mixed oil, enabling the oil pump to function as a mixing oil pump. By controlling the duty cycle of the control signal of the electromagnet 2, the duration for which the first valve core 5 is connected to the lubricating oil inlet 13 and the fuel inlet 14 can be further controlled, thereby controlling the proportion of the mixed oil.

[0033] Since the proportion of fuel in the oil mixture is much greater than that of lubricating oil, the connection time of the route from fuel inlet 14, fuel pump, to fuel outlet 12 is longer. Therefore, most of the oil mixture will enter the engine from fuel outlet 12 to complete combustion, which meets the usage requirements.

[0034] The lubricating oil outlet 11 and fuel outlet 12 connected to the second valve core 4 are high-pressure ends, therefore the second valve core 4 uses a ceramic sealing ball to ensure sufficiently excellent sealing performance. The lubricating oil inlet 13 and fuel inlet 14 connected to the first valve core 5 are low-pressure ends, and the requirements for sealing performance are not high, so a small amount of leakage can be allowed. Therefore, a rod-type spool valve can be used.

[0035] Specifically, the second valve core 4 uses dual silicon nitride ceramic balls (HV1500), with a leakage rate of ≤0.05mL / min at 3MPa, and helium leak detection is performed. The first valve core 5 adopts an H7 / g6 grade valve stem clearance and a fluororubber O-ring (temperature resistant to 230℃). It allows fuel to penetrate into the lubricating oil at a rate of 1.5mL / min@0.5MPa. A mixing ratio of <3% does not affect the function.

[0036] Due to the structural differences between the second valve core 4 and the first valve core 5, the resistance they generate during movement also differs. Therefore, the connecting rod 6 is connected to the first valve core 5 via the connecting rod spring 61 to buffer the resistance difference between them. Simultaneously, the low resistance of the first valve core 5 allows for the mixing of fuel and lubricating oil by controlling its reciprocating motion.

[0037] The above description is merely an embodiment of this utility model and does not limit the patent scope of this utility model. Any equivalent structural or procedural transformations made using the content of this utility model specification, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this utility model.

Claims

1. A dual-way three-position valve for a dual-mode fuel-lubricating oil system in a multi-electric aircraft engine, characterized in that: The device includes a housing, an electromagnet, a first valve core, a second valve core, and a connecting rod. A second outlet, a pump outlet, a first outlet, a second inlet, a pump inlet, and a first inlet are sequentially arranged through the housing. The second valve core, the connecting rod, and the first valve core are sequentially arranged inside the housing. One end of the housing is closed, and the other end has the electromagnet connected to the first valve core. The connecting rod is slidably connected to the housing and divides the housing into two sections: one section connects the second outlet, the pump outlet, and the first outlet; the other section connects the second inlet, the pump inlet, and the first inlet. One configuration connects the second outlet and the pump outlet, and simultaneously the second inlet and the pump inlet; the other configuration connects the first outlet and the pump outlet, and simultaneously the first inlet and the pump inlet.

2. The dual three-way valve for a dual-mode fuel-lubricating oil system in a multi-electric aircraft engine according to claim 1, characterized in that: A second outlet, a first outlet, a second inlet, and a first inlet are sequentially provided through one side of the housing; on the other side opposite to the aforementioned four openings, a pump outlet is provided through the housing between the second outlet and the first outlet, and a pump inlet is provided through the housing between the first inlet and the second inlet.

3. The dual three-way valve for a dual-mode fuel-lubricating oil system of a multi-electric aircraft engine according to claim 1 or 2, characterized in that: The housing is provided with a valve sleeve, which separates annular connecting cavities at the positions of the second outlet, pump outlet, first outlet, pump inlet, first inlet and second inlet, and each connecting cavity is provided with an opening leading to the valve sleeve; the valve sleeve is provided with the second valve core, the connecting rod and the first valve core in sequence, one end of the valve sleeve is closed and the other end is open, so that the electromagnet can be connected to the first valve core.

4. The dual three-way valve for a dual-mode fuel-lubricating oil system of a multi-electric aircraft engine according to claim 3, characterized in that: The valve sleeve is provided with an intermediate valve sleeve, and the connecting rod is slidably connected to the intermediate valve sleeve, dividing the valve sleeve into two areas.

5. The dual three-way valve for a dual-mode fuel-lubricating oil system in a multi-electric aircraft engine according to claim 4, characterized in that: The second valve core includes a valve seat, a second spring, a second push rod, and a sealing unit. The valve seat is located inside the valve sleeve, with a second valve cavity in the middle that communicates with the pump outlet. Both ends are respectively provided with channels that connect the second outlet and the first outlet to the two ends of the second valve cavity. The middle section of the sealing unit passes through the second valve cavity, and both ends are located in the two channels. One end of the sealing unit abuts against the closed end of the valve sleeve through the second push rod and the second spring in sequence, and the other end abuts against the connecting rod.

6. The dual three-way valve for a dual-mode fuel-lubricating oil system of a multi-electric aircraft engine according to claim 5, characterized in that: The sealing unit includes a first push rod passing through the valve cavity and ceramic sealing balls located at both ends of the valve cavity. The ceramic sealing balls can abut against the openings at both ends of the valve cavity to seal the valve cavity.

7. The dual three-way valve for a dual-mode fuel-lubricating oil system of a multi-electric aircraft engine according to claim 5 or 6, characterized in that: One end of the connecting rod passes through the valve seat and abuts against the sealing unit, while also abutting against the valve seat via a first spring. The middle section slides into the intermediate valve sleeve, and the other end abuts against the first valve core via a connecting rod spring.

8. The dual three-way valve for a dual-mode fuel-lubricating oil system of a multi-electric aircraft engine according to claim 7, characterized in that: The two ends of the first valve core are slidably connected to the valve sleeve, and the outer side of the middle section is provided with an annular first valve cavity. The first valve cavity connects the second inlet to the pump inlet, or connects the first inlet to the pump inlet.

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