Flow resistance ring, air flow resistance assembly, engine and flow resistance assembly manufacturing method

Abstract

The invention relates to the technical field of aero-engines, in particular to a flow resistance ring, an air flow resistance assembly, an engine and a flow resistance assembly manufacturing method. The flow resistance ring comprises a flow resistance ring sleeve, the flow resistance ring sleeve is a hollow pipeline and used for gas circulation, and the flow resistance ring sleeve comprises a head end and a tail end in the axial direction; the multiple flow resistance plates are arranged on the inner side of the flow resistance ring sleeve in the axial direction of the flow resistance ring sleeve; the flow resistance plate is in a funnel shape and is provided with a wide-opening end and a narrow-opening end, the wide-opening end is fixedly arranged on the inner surface of the flow resistance ring sleeve, and the flow resistance plate extends inwards in the radial direction of the flow resistance ring sleeve and extends towards the tail end in the axial direction of the flow resistance ring sleeve to form the narrow-opening end for gas to penetrate through; and gas entering from the tail end forms vortex among the plurality of flow resistance plates so as to reduce the pressure of gas exhausted from the head end. The flow resistance plate and the flow resistance ring sleeve do not have relative mechanical motion, stability is high, failure is not prone to occurring, the structure is simple, reliability is high, and gas backflow can be prevented.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aeroengines, and particularly to a flow resistance ring, an air flow resistance assembly, an engine, and a manufacturing method of the flow resistance assembly. Background Art

[0002] The working conditions of aeroengine components are harsh. Especially for turbine blades, the gas temperature can reach above 1900K, exceeding the temperature resistance range for the material to work stably for a long time. To meet the strength requirements of engine parts and improve the reliability of the engine, it is necessary to cool them. One of the cooling methods is to guide low-temperature gas from the compressor to the high-temperature turbine components to form a gas film on the surface of the turbine blade components to isolate the high-temperature gas and reduce its surface temperature. To prevent the high-temperature gas of the turbine from flowing back into the compressor during the aeroengine test or operation and damaging the engine components, a check valve is generally required to be set in the air intake pipe, that is, only allowing the gas to flow from the compressor to the turbine and not allowing the gas to flow from the turbine to the compressor.

[0003] For the current research on aeroengine technology, there are still the following problems: Most of the existing check valves of aeroengines are passive, relying on the gas pressure to realize the movement of the valve flap and achieve the function of one-way flow. During the operation of the engine, as the gas pressure changes, the valve flap rotates around the core shaft, resulting in wear of the core shaft and jamming of the valve flap, bringing great potential safety hazards to the operation of the engine. Summary of the Invention

[0004] To overcome the problems existing in the related art, the exemplary embodiments of the present disclosure provide a flow resistance ring, an air flow resistance assembly, an engine, and a manufacturing method of the flow resistance assembly.

[0005] The exemplary embodiment of the first aspect of the present disclosure provides a flow resistance ring, which may include: a flow resistance ring sleeve, the flow resistance ring sleeve is a hollow pipe for gas flow, and the flow resistance ring sleeve includes a head end and a tail end along the axial direction; a plurality of flow resistance plates, the plurality of flow resistance plates are arranged on the inner side of the flow resistance ring sleeve along the axial direction of the flow resistance ring sleeve; the flow resistance plates are in a funnel shape, having a wide mouth end and a narrow mouth end, the wide mouth end is fixedly arranged on the inner surface of the flow resistance ring sleeve, and the flow resistance plates extend radially inward along the flow resistance ring sleeve and extend axially along the flow resistance ring sleeve towards the tail end to form a narrow mouth end for gas to pass through; the gas entering from the tail end forms a vortex between the plurality of flow resistance plates to reduce the gas pressure discharged from the head end.

[0006] In some embodiments, the flow resistance ring may further include: a first flange interface and a second flange interface; the first flange interface is located at the head end of the flow resistance ring and can be connected to the second flange interface of another flow resistance ring; the second flange interface is located at the tail end of the flow resistance ring and can be connected to the first flange interface of another flow resistance ring.

[0007] In some embodiments, the material of the flow resistance plate may be a shape memory alloy; when the gas temperature in the flow resistance ring is greater than or equal to the temperature threshold, the opening area of the narrow end of the flow resistance plate becomes smaller.

[0008] In some embodiments, the included angle between the flow resistance plate and the inner wall of the flow resistance ring sleeve may be greater than or equal to 30 degrees and less than or equal to 60 degrees.

[0009] Second, according to some other exemplary embodiments, the present disclosure also provides an air flow resistance assembly for an engine, wherein the air flow resistance assembly may include:

[0010] A flow resistance ring as in the first aspect or a plurality of flow resistance rings as in the first aspect connected end to end; a first transfer pipeline, which is a hollow pipeline, the first end of the first transfer pipeline is connected to the first end of the flow resistance ring, and the second end of the first transfer pipeline is used to communicate with the compressor of the engine; a second transfer pipeline, which is a hollow pipeline, the first end of the second transfer pipeline is connected to the tail end of the flow resistance ring, and the second end of the second transfer pipeline is used to communicate with the turbine of the engine; the gas that enters the flow resistance ring from the tail end of the flow resistance ring sleeve through the second transfer pipeline from the turbine forms a vortex between the plurality of flow resistance plates to reduce the gas pressure discharged from the first end.

[0011] In some embodiments, the air flow resistance assembly may further include: a seal; the seal is provided at the first end and the tail end of the flow resistance ring for sealing to prevent gas leakage.

[0012] In some embodiments, the air flow resistance assembly may further include: a clamp; the clamp is sleeved on the first end and the tail end of the flow resistance ring for fixing the flow resistance ring and the transfer pipeline.

[0013] Third, according to some other exemplary embodiments, the present disclosure also provides an engine, wherein the engine may include: an air flow resistance assembly for an engine as in the second aspect; an engine housing, a combustion chamber is provided inside the engine housing, a compressor is provided on the first side of the combustion chamber, and a turbine is provided on the second side of the combustion chamber; the air flow resistance assembly is disposed outside the engine housing, the compressor side of the engine housing is connected to the second end of the first transfer pipeline of the air flow resistance assembly; the turbine side of the engine housing is connected to the second end of the second transfer pipeline of the air flow resistance assembly; gas can flow from the compressor side through the air flow resistance assembly to the turbine side; gas can flow from the turbine side through the air flow resistance assembly, and a vortex is formed between the plurality of flow resistance plates to reduce the gas pressure discharged from the compressor side.

[0014] In some embodiments, the engine may further include: a first adapter flange disposed outside the engine housing, communicating with the engine housing, located on one side of the compressor, and connected to the second end of the first transfer pipeline; a second adapter flange disposed on the outer surface of the engine housing, communicating with the engine housing, located on one side of the turbine, and connected to the second end of the second transfer pipeline.

[0015] Fourthly, according to some other exemplary embodiments, the present disclosure further provides a manufacturing method for an air flow resistance assembly for an engine as in the second aspect, which may include: obtaining the gas pressure loss of the flow resistance ring sleeve from the tail end to the head end; obtaining the pressure difference between the maximum pressure on the turbine side and the minimum pressure on the compressor side when the engine is in the working state; determining one flow resistance ring or a plurality of flow resistance rings connected end to end based on the gas pressure loss value and the pressure difference, wherein the total gas pressure loss of one flow resistance ring or a plurality of flow resistance rings connected end to end is greater than or equal to the pressure difference; connecting one flow resistance ring or a plurality of flow resistance rings connected end to end to the first transfer pipeline and the second transfer pipeline.

[0016] In some embodiments, determining one flow resistance ring or a plurality of flow resistance rings connected end to end based on the gas pressure loss value and the pressure difference may include: the total gas pressure loss of one flow resistance ring or a plurality of flow resistance rings connected end to end is greater than or equal to the pressure difference and less than or equal to a first threshold.

[0017] The technical solutions provided by the embodiments of the present disclosure may include the following beneficial effects: By providing a flow resistance ring and using a plurality of flow resistance plates fixedly connected to the inner side of the flow resistance ring sleeve, when the gas backflows from the tail end to the head end of the flow resistance ring sleeve, the backflow air flow forms a vortex between the plurality of flow resistance plates, thereby effectively reducing the gas pressure discharged from the head end, and effectively preventing gas backflow. The flow resistance plates are fixedly connected to the inner side of the flow resistance ring sleeve, and there is no relative mechanical movement between the flow resistance plates and the flow resistance ring sleeve, so the structure is simple and the reliability is high.

[0018] It should be understood that the above general description and the following detailed description are only exemplary and explanatory, and cannot limit the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] By describing the exemplary embodiments of the present disclosure in conjunction with the drawings, the present disclosure can be better understood. In the drawings:

[0020] Figure 1 is a schematic cross-sectional structure diagram of a flow resistance ring shown according to an exemplary embodiment of the present disclosure;

[0021] Figure 2 is a schematic structure diagram of a flow resistance ring shown according to an exemplary embodiment of the present disclosure;

[0022] Figure 3It is a schematic diagram of the gas flow direction from the head end to the tail end within the flow resistance ring shown according to an exemplary embodiment of the disclosure;

[0023] Figure 4 It is a schematic diagram of the gas flow direction from the tail end to the head end within the flow resistance ring shown according to an exemplary embodiment of the disclosure;

[0024] Figure 5 It is a schematic diagram of the air flow resistance component structure for an engine shown according to an exemplary embodiment of the disclosure;

[0025] Figure 6 It is a schematic diagram of the engine structure shown according to an exemplary embodiment of the disclosure. Detailed implementation manners

[0026] The following will describe the detailed implementation manners of the present disclosure. It should be noted that during the specific description of these implementation manners, for the sake of concise description, it is impossible for this specification to describe all features of the actual implementation manners in detail. It should be understood that during the actual implementation process of any implementation manner, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer and to meet system-related or business-related restrictions, various specific decisions are often made, and these will also change from one implementation manner to another. In addition, it can also be understood that although the efforts made during such a development process may be complex and lengthy, for those of ordinary skill in the art related to the content disclosed in the present disclosure, some design, manufacturing, or production changes based on the technical content disclosed in the present disclosure are only conventional technical means and should not be understood as the content of the present disclosure being insufficient.

[0027] Unless otherwise defined, the technical terms or scientific terms used in the claims and the specification should have the ordinary meaning understood by those of ordinary skill in the technical field to which the present disclosure belongs. The "first", "second", and similar terms used in the specification and claims of the present patent application do not indicate any order, quantity, or importance, but are only used to distinguish different components. The terms such as "a" or "one" do not indicate a quantity limitation, but indicate that there is at least one. The terms such as "including" or "comprising" mean that the elements or objects appearing before "including" or "comprising" cover the elements or objects listed after "including" or "comprising" and their equivalent elements, and do not exclude other elements or objects. The terms such as "connected" or "coupled" are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0028] An aeroengine includes a compressor, a combustion chamber, and a turbine. During engine operation, gas enters from the compressor, is compressed by the compressor and then enters the combustion chamber to mix with fuel for combustion, and the generated high-temperature gas flows towards the turbine. During engine operation, since the gas temperature at the turbine is too high, to ensure the reliability of the engine, it needs to be cooled. Therefore, an air intake pipe is provided to connect the compressor and the turbine, and the low-temperature gas at the compressor is guided to the high-temperature turbine. To prevent the high-temperature gas at the turbine from flowing back into the compressor and damaging components, the existing design generally sets a check valve at the air intake pipe to achieve the one-way flow of gas in the air intake pipe from the compressor to the turbine. However, due to the air pressure change during engine operation, the check valve is prone to problems such as mandrel wear and valve disc jamming failure, which may cause the high-temperature gas to flow back and damage the engine, posing a great safety hazard. To solve the aforementioned technical problems, as Figure 1 shown, a flow resistance ring 100 is provided. Among them, the flow resistance ring 100 may include: a flow resistance ring sleeve 110, the flow resistance ring sleeve 110 is a hollow pipe for gas flow, and the flow resistance ring sleeve 110 includes a head end and a tail end along the axial direction; a plurality of flow resistance plates 120, the plurality of flow resistance plates 120 are arranged on the inner side of the flow resistance ring sleeve 110 along the axial direction of the flow resistance ring sleeve 110; the flow resistance plate 120 is in a funnel shape, having a wide mouth end and a narrow mouth end, the wide mouth end is fixedly arranged on the inner surface of the flow resistance ring sleeve 110, and the flow resistance plate 120 extends radially inward along the flow resistance ring sleeve 110 and extends axially towards the tail end of the flow resistance ring sleeve 110 to form a narrow mouth end for gas to pass through; the gas entering from the tail end forms a vortex between the plurality of flow resistance plates 120 to reduce the gas pressure discharged from the head end.

[0029] Among them, the flow resistance ring sleeve 110 can be a cylindrical hollow pipe. The flow resistance ring sleeve 110 can be made of a high-temperature resistant rigid material. The material of the flow resistance ring sleeve 110 can be determined by the working environment and the vibration environment during operation. The flow resistance ring sleeve 110 can be made of stainless steel material, with corrosion resistance, high-temperature resistance, good weldability, and oxidation resistance at high temperatures; the flow resistance ring sleeve 110 can also be made of nickel-based alloy material, with ultra-high temperature resistance, oxidation resistance, and fatigue resistance; the flow resistance ring sleeve 110 can also be made of titanium alloy material, with good plasticity and being lighter. When the flow resistance ring sleeve 110 is made of titanium alloy material, it is necessary to evaluate the fire prevention plan of the flow resistance ring sleeve 110 to prevent the titanium alloy from catching fire. The flow resistance ring sleeve 110 can include a head end and a tail end along the axial direction. Gas can flow inside the flow resistance ring sleeve 110. The gas can flow into the interior of the flow resistance ring sleeve 110 through the head end and flow out through the tail end, or the gas can also flow into the interior of the flow resistance ring sleeve 110 through the tail end and flow out through the head end. The head end and the tail end of the flow resistance ring sleeve 110 can be connected to other components. Flange interfaces can be provided at the head end and the tail end of the flow resistance ring sleeve 110 for docking and fixing through the flange interfaces; threads can also be provided on the circumferential sides of the head end and the tail end of the flow resistance ring sleeve 110 for fixed connection with other components through the threads. A plurality of flow resistance plates 120 are arranged inside the flow resistance ring sleeve 110. The flow resistance plates 120 can be fixedly connected to the flow resistance ring sleeve 110, or the flow resistance plates 120 can also be a structure integrally formed with the flow resistance ring sleeve 110; the flow resistance plates 120 and the flow resistance ring sleeve 110 can be fixedly connected through sheet metal welding, which is light and easy to process; the flow resistance plates 120 and the flow resistance ring sleeve 110 can also be integrally formed by machining, die forging, and casting methods, with higher strength and precision; the flow resistance plates 120 and the flow resistance ring sleeve 110 can also be integrally formed by 3D printing, with good structural adaptability and convenient processing. A plurality of flow resistance plates 120 are axially distributed inside the flow resistance ring sleeve 110 along the flow resistance ring sleeve 110. A plurality of flow resistance plates 120 can be evenly distributed inside the flow resistance ring sleeve 110, and the distances between a plurality of flow resistance plates 120 can be different. The flow resistance plates 120 can be in a funnel shape, having a wide mouth section and a narrow mouth end. The wide mouth end of the flow resistance plate 120 can have the same size and shape as the inner surface of the flow resistance ring sleeve 110. The flow resistance plates 120 can be fixedly arranged on the inner surface of the flow resistance ring sleeve 110, extending radially inward along the flow resistance ring sleeve 110 and extending axially along the flow resistance ring sleeve 110 towards the tail end to form a narrow mouth end for gas to pass through. The narrow mouth ends of a plurality of flow resistance plates 120 have the same direction, facing the tail end of the flow resistance ring sleeve 110. The narrow mouth ends of a plurality of flow resistance plates 120 can be in the shape of round holes or square holes; the lengths by which a plurality of flow resistance plates 120 extend from the wide mouth end to the narrow mouth end can be the same or different; the air flow areas at the narrow mouth ends of a plurality of flow resistance plates 120 can be the same or different.The flow resistance plate 120 can be a hollow frustum. The hollow channel of the hollow frustum can be conical, having a wide mouth end and a narrow mouth end. The outer peripheral side of the wide mouth end of the hollow frustum can have the same size and shape as the inner surface of the flow resistance ring sleeve 110. The wide mouth end of the hollow frustum can be fixedly installed on the inner surface of the flow resistance ring sleeve 110 and is coaxially arranged with the flow resistance ring sleeve 110. The wide mouth end of the flow resistance plate 120 is fixedly connected to the flow resistance ring sleeve 110 or integrally formed with the flow resistance ring sleeve 110; the narrow mouth end of the flow resistance plate 120 faces the tail end of the flow resistance ring sleeve 110. For example. Figure 3 As shown, when the gas flows from the head end to the tail end of the flow resistance ring sleeve 110, that is, when the gas flows from the wide mouth section of the flow resistance plate 120 to the narrow mouth end, the gas flow resistance is very small; as Figure 4 shown, when the gas flows from the tail end to the head end of the flow resistance ring sleeve 110, that is, from the narrow mouth end of the flow resistance plate 120 to the wide mouth end, part of the gas in the flow resistance ring 100 flows from the narrow mouth end of the previous flow resistance plate 120 along the flow resistance plate 120 into the cavity between the front and rear flow resistance plates 120, and then flows reversely along the rear flow resistance plate to the narrow mouth end of the front flow resistance plate, thereby forming a vortex between the two axially arranged flow resistance plates 120, increasing the resistance of the gas, effectively reducing the gas pressure discharged from the head end, that is, the pressure drop of the gas when passing through the flow resistance ring 100 is very large.

[0030] By setting the flow resistance ring 100 and fixing the flow resistance plate 120 inside the flow resistance ring sleeve 110, there is no relative mechanical movement between the flow resistance plate 120 and the flow resistance ring sleeve 110, with high stability, not easily failing, simple structure and high reliability. Through the funnel-shaped design of the flow resistance plate 120, the resistance received by the air when entering the flow resistance ring 100 from the head end or the tail end is different. The gas entering the flow resistance ring 100 from the tail end of the flow resistance ring sleeve 110 forms a vortex between multiple flow resistance plates 120, and the pressure decreases when flowing to the head end and being discharged, which can prevent gas backflow.

[0031] In some embodiments, such as Figure 1 、 2As shown, the flow resistance ring 100 may further include: a first flange interface 130 and a second flange interface 140; the first flange interface 130 is located at the head end of the flow resistance ring sleeve 110 and can be connected to the second flange interface 140 of another flow resistance ring; the second flange interface 140 is located at the tail end of the flow resistance ring sleeve 110 and can be connected to the first flange interface 130 of another flow resistance ring. This facilitates production, manufacturing or procurement and effectively reduces the usage cost. When multiple flow resistance rings are provided, the flow resistance rings 100 can be connected end to end through the first flange interface 130 and the second flange interface 140. The first flange interface 130 is located at the head end of the flow resistance ring sleeve 110 and can be connected to the second flange interface 140 located at the tail end of another flow resistance ring 100. The first flange interface 130 and the second flange interface 140 may be a female head and a male head that are correspondingly matched. The female head may be a hollow cylinder, one end of which is fixedly connected to the head end of the flow resistance ring sleeve 110. The other end of the female head may have a concave fixing groove for butt-joint installation with the male head. The male head may be a hollow cylinder, one end of which is fixedly connected to the tail end of the flow resistance ring sleeve 110, and the other end may be provided with an outwardly convex positioning boss that can be butted against the concave fixing groove at the end of the female head; the female heads and male heads of two flow resistance rings 100 can be butted against each other, while the female heads of two flow resistance rings 100 and the female heads, and the male heads and male heads cannot be butted and installed; since when air flows into the flow resistance ring 100 from the head end, the gas is less affected by resistance, while when it flows into the interior of the flow resistance ring 100 from the tail end, it is subject to greater resistance and the pressure drop is larger. Therefore, when used on the engine intake pipe, attention needs to be paid to the direction of the flow resistance ring 100. When the flow resistance ring 100 is reversely connected, a large amount of high-temperature gas at the turbine will flow back to the compressor, damaging the engine and causing danger. Through the design of the female head and male head of the first flange interface 130 and the second flange interface 140, it is possible to avoid incorrect connection and reverse connection during the installation of multiple flow resistance rings 100, ensure that the direction of the internal flow resistance plate 120 is the same when multiple flow resistance rings are connected to each other, and improve the safety of the flow resistance ring and the engine.

[0032] In some embodiments, the material of the flow resistance plate 120 can be a shape memory alloy; when the gas temperature in the flow resistance ring 100 is greater than or equal to the temperature threshold, the opening area of the narrow end of the flow resistance plate 120 becomes smaller. The flow resistance plate 120 can be a shape memory alloy. When the gas temperature in the flow resistance ring 100 is lower than the temperature threshold, the flow resistance plate 120 maintains its current configuration unchanged; when the gas temperature in the flow resistance ring 100 is greater than or equal to the temperature threshold, the flow resistance plate 120 deforms, the narrow end of the flow resistance plate 120 contracts inward, the opening area of the narrow end of the flow resistance plate 120 becomes smaller, the resistance of the gas flowing from the narrow end to the wide end of the flow resistance plate 120 increases, the pressure drop of the flow resistance plate 120 increases, and it can adapt to high-temperature environments and change the pressure drop of the flow resistance plate 120. When the engine is operating normally, the gas temperature in the flow resistance ring 100 is lower than the temperature threshold, the gas enters from the head end of the flow resistance ring sleeve 110, passes through the wide end of the flow resistance plate 120, flows to the narrow end, and finally flows out from the tail end, and the configuration of the flow resistance plate 120 does not change; when gas backflow occurs, the high-temperature gas at the turbine enters from the tail end of the flow resistance ring sleeve 110, flows through the narrow section of the flow resistance plate 120 to the wide end, and forms a vortex between two axially arranged flow resistance plates 120, increasing the resistance of the gas, and the air pressure drops when flowing out from the head end of the flow resistance ring sleeve 110. When the gas temperature is greater than the temperature threshold, the flow resistance plate 120 can deform, the narrow end of the flow resistance plate 120 contracts inward, the opening area of the narrow end of the flow resistance plate 120 becomes smaller, increasing the resistance of the backflow gas when flowing out from the head end of the flow resistance ring sleeve 110 and effectively preventing gas backflow.

[0033] In some embodiments, the surface of the flow resistance plate 120 and the inner wall of the flow resistance ring sleeve 110 can have a coating for reducing flow resistance and protecting the internal structure of the flow resistance ring 100. The selection of the coating material can be based on the actual operating conditions of the flow resistance ring 100. When the flow resistance ring 100 is in a temperature environment of less than or equal to 650 °C for a long time, the surface of the flow resistance plate 120 and the inner wall of the flow resistance ring sleeve 110 can be plated with a silver coating. The silver coating has good thermal conductivity and corrosion resistance, which can make the surface of the flow resistance plate 120 and the flow resistance ring sleeve 110; when the flow resistance ring 100 is in a temperature environment of greater than or equal to 650 °C and less than or equal to 760 °C for a long time, the surface of the flow resistance plate 120 and the inner wall of the flow resistance ring sleeve 110 can be pre-plated with gold and then plated with silver on the outer layer. The pre-plating of gold can improve the compactness of the external silver coating, prevent the damage and aging of the flow resistance ring 100 caused by the shedding of the coating, and improve the service life of the flow resistance ring 100; when the flow resistance ring 100 is in a temperature environment of greater than or equal to 760 °C and less than or equal to 926 °C for a long time, the surface of the flow resistance plate 120 and the inner wall of the flow resistance ring sleeve 110 can be plated with gold. The gold coating surface is dense, has high stability and good safety, and can make the flow resistance plate 120 and the flow resistance ring sleeve 110 adapt to higher working temperatures.

[0034] In some embodiments, the angle between the flow resistance plate 120 and the inner wall of the flow resistance ring sleeve 110 may be greater than or equal to 30 degrees and less than or equal to 60 degrees. To prevent gas backflow, the gas flowing from the head end to the tail end of the flow resistance ring sleeve 110 needs to encounter a relatively large flow resistance. The angle between the flow resistance plate 120 and the inner wall of the flow resistance ring sleeve 110 may be greater than or equal to 30 degrees. At this time, cavities are formed between multiple adjacent flow resistance plates 120. When the gas flows from the tail end to the head end of the flow resistance ring sleeve 110, part of the gas flows into the cavities between multiple adjacent flow resistance plates 120 along the flow resistance plate 120 and circulates along the adjacent flow resistance plates 120, forming eddy currents in the cavities between multiple adjacent flow resistance plates 120, so that the flow resistance of the gas increases; when the angle between the flow resistance plate 120 and the inner wall of the flow resistance ring sleeve 110 is less than 30 degrees, since the part of the flow resistance plate 120 extending into the flow resistance ring sleeve 120 is close to the inner wall of the flow resistance ring sleeve 110 and the ventilation channel in the center of the flow resistance plate 120 is relatively large, when the gas flows from the tail end to the head end of the flow resistance ring sleeve 110, less gas flows into the cavities between multiple adjacent flow resistance plates 120 to form eddy currents, and the flow resistance of the gas is relatively small; therefore, when the angle between the flow resistance plate 120 and the inner wall of the flow resistance ring sleeve 110 is greater than or equal to 30 degrees, the flow resistance ring 100 has better performance in preventing gas backflow. At the same time, to ensure that the gas flowing from the head end to the tail end of the flow resistance ring sleeve 110 can flow normally, the flow resistance of the gas flowing from the head end to the tail end of the flow resistance ring sleeve 110 should be small. The angle between the flow resistance plate 120 and the inner wall of the flow resistance ring sleeve 110 may be less than or equal to 60 degrees. When the angle between the flow resistance plate 120 and the inner wall of the flow resistance ring sleeve 110 is greater than or equal to 60 degrees, the flow resistance plate is close to being perpendicular, and the ventilation channel in the center of the flow resistance plate 120 is relatively small. The flow resistance of the gas flowing from the head end to the tail end of the flow resistance ring sleeve 110 is relatively large, which is not conducive to gas flow; when the angle between the flow resistance plate 120 and the inner wall of the flow resistance ring sleeve 110 is less than or equal to 60 degrees, the flow resistance of the gas flowing from the head end to the tail end of the flow resistance ring sleeve 110 is small, and the gas flowing from the head end to the tail end of the flow resistance ring sleeve 110 can flow normally.

[0035] In some embodiments, the distance between multiple flow resistance plates 120 may be greater than or equal to 10 millimeters and less than or equal to 50 millimeters. When the distance between multiple flow resistance plates 120 is greater than or equal to 10 millimeters, the cavities formed between multiple flow resistance plates 120 can accommodate a certain amount of gas, enabling the gas to enter the cavities for circulating flow. When the distance between multiple flow resistance plates 120 is less than or equal to 50 millimeters, multiple flow resistance plates 120 can effectively guide the gas to circulate, ensuring that the gas entering the cavities formed between multiple flow resistance plates 120 can circulate to form eddy currents. The number of flow resistance plates 120 may be less than or equal to 5. When the number of flow resistance plates 120 is less than or equal to 5, it can ensure that the gas flowing from the tail end to the head end of the flow resistance ring sleeve 110 encounters a certain air flow resistance. While preventing backflow, it can ensure that the air flow resistance of the gas flowing from the head end to the tail end of the flow resistance ring sleeve 110 is relatively small and can flow.

[0036] Based on the same inventive concept, as Figure 5 shown, the present disclosure also provides an air flow resistance assembly 200 for an engine. Among them, the air flow resistance assembly 200 may include: a flow resistance ring 100 of any of the foregoing embodiments or a plurality of flow resistance rings 100 of any of the foregoing embodiments connected end to end; one or more flow resistance rings 100 may be provided. When a plurality of flow resistance rings are provided, the flow resistance rings may be connected to each other. The tail end of the flow resistance ring sleeve 110 is connected to the head end of another flow resistance ring sleeve, so that the directions of the internal flow resistance plates 120 of the plurality of flow resistance rings 100 are the same.

[0037] A first transfer pipeline 210, which may be a hollow pipeline. The first transfer pipeline 210 may be made of a high-temperature resistant rigid material. The first transfer pipeline 210 may be a bent pipeline, which is convenient for connecting the engine and the flow resistance ring 100. The first end of the first transfer pipeline 210 may be connected to the head end of the flow resistance ring sleeve 110, and the second end of the first transfer pipeline 210 may be used to communicate with the compressor of the engine; when the head end of the flow resistance ring sleeve 110 is provided with a female head for docking, the first end of the first transfer pipeline 210 may be provided with a male head that can be docked with the head end of the flow resistance ring sleeve 110. A second transfer pipeline 220, which may be a hollow pipeline. The second transfer pipeline 220 may be made of a high-temperature resistant rigid material. The second transfer pipeline 220 may be a bent pipeline, which is convenient for connecting the engine and the flow resistance ring 100. The first end of the second transfer pipeline 220 may be connected to the tail end of the flow resistance ring sleeve 110, and the second end of the second transfer pipeline 220 may be used to communicate with the turbine of the engine; when the tail end of the flow resistance ring sleeve 110 is provided with a male head for docking, the first end of the second transfer pipeline 220 may be provided with a female head that can be docked with the tail end of the flow resistance ring sleeve 110. Gas may enter the air flow resistance assembly 200 through the second end of the first transfer pipeline 210 from the compressor, pass through the flow resistance ring 100, flow from the tail end of the flow resistance ring sleeve 110 to the second transfer pipeline 220, and finally flow to the turbine. Since the gas flows from the wide-mouth end to the narrow-mouth end of the flow resistance plate 120 during circulation, the resistance received by the gas is very small and the air flow is less obstructed; when the gas backflows from the turbine to the air flow resistance assembly 200, the gas enters the air flow resistance assembly 200 through the second end of the second transfer pipeline, passes through the flow resistance ring 100, and flows from the head end of the flow resistance ring sleeve 110 to the first transfer pipeline 210, and backflows to the compressor. Since the gas backflows from the narrow-mouth end to the wide-mouth end of the flow resistance plate 120, the air flow is obstructed. The gas passing through the second transfer pipeline 220 from the turbine and entering the flow resistance ring 100 from the tail end of the flow resistance ring sleeve 110 forms eddy currents between the plurality of flow resistance plates 120, so that the resistance received by the gas is large, the pressure drop increases, and the air flow is obstructed, so as to reduce the pressure of the gas discharged from the head end. When used on an engine, it can effectively prevent gas backflow.

[0038] In some embodiments, the air flow resistance assembly 200 for an engine may further include a connecting pipe, which is a hollow pipeline. The air flow resistance assembly 200 may include one flow resistance ring 100 or multiple flow resistance rings 100 connected end to end. Since the installation position of the air flow resistance assembly 200 on the engine is fixed, the reserved distance between the first end of the first connecting pipe 210 and the first end of the second connecting pipe 220 is fixed. When the total length of one flow resistance ring 100 or multiple flow resistance rings 100 connected end to end is less than the reserved distance, a hollow connecting pipe can be installed to connect the flow resistance ring 100 to the first connecting pipe 210 or connect the flow resistance ring 100 to the second connecting pipe 220. When multiple flow resistance rings 100 are connected end to end, the connecting pipe can be installed between two flow resistance rings 100 to ensure the closure of the flow channel between the air flow resistance assembly 200 and the engine. Male or female connectors for butt-connecting with the flow resistance ring 100 can be provided at both ends of the connecting pipe to facilitate the connection and installation of the air flow resistance assembly 200.

[0039] In some embodiments, as Figure 5 shown, the air flow resistance assembly 200 may further include: a seal 230; the seal 230 is provided at the head and tail ends of the flow resistance ring for sealing to prevent gas leakage. The seal 230 can be a standard part conforming to the British standard, which is convenient for production, manufacturing or procurement and reduces the use cost. The seal 230 can be a sealing gasket or a sealing ring sleeved on the outer sides of the head and tail ends of the flow resistance ring sleeve 110. The seal 230 can be made of metal, with good sealing effect and can maintain good sealing performance in high-temperature environments, being safe, reliable and having a long service life.

[0040] In some embodiments, as Figure 5 shown, the air flow resistance assembly 200 may further include: a clamp 240; the clamp 240 is sleeved on the head and tail ends of the flow resistance ring sleeve 110 for fixing the flow resistance ring 100 and the connecting pipe. The clamp 240 can be a grooved clamp, which is locked and fixed by bolts; the clamp 240 can be made of high-temperature-resistant metal; gaskets or rubber can be provided on the inner ring of the clamp 240 for fixing and sealing the flow resistance ring 100 to prevent friction and wear between the clamp 240 and the flow resistance ring 100. Installing the clamp 240 can facilitate the fixing and locking of the flow resistance ring 100 and the connecting pipe, prevent the flow resistance ring 100 and the connecting pipe from detaching, and prevent gas leakage.

[0041] Based on the same inventive concept, as Figure 6As shown in the figure, the present disclosure also provides an engine 300. The engine 300 may include: an air flow resistance component 200 for the engine according to any of the foregoing embodiments; an engine housing 310 with a combustion chamber provided inside. A compressor is arranged on the first side of the combustion chamber, and a turbine is arranged on the second side of the combustion chamber. The air flow resistance component 200 is arranged on the outer side of the engine housing 310. The compressor side of the engine housing 310 is connected to the second end of the first transfer pipeline 210 of the air flow resistance component 200. The turbine side of the engine housing 310 is connected to the second end of the second transfer pipeline 220 of the air flow resistance component 200. The interior of the engine housing 310 can be divided into three sequentially arranged chambers, with a compressor, a combustion chamber, and a turbine arranged in the three chambers respectively. Gas can flow from the compressor side through the air flow resistance component 200 to the turbine side. The gas can pass through the first transfer pipeline 210 from the compressor side and flow into the flow resistance ring 100. The gas flows from the head end to the tail end of the flow resistance ring sleeve 110 and flows into the turbine side through the second transfer pipeline 220. The gas flow resistance is small, and the gas can flow smoothly. The low-temperature gas is poured into the turbine side to cool the turbine. Gas can flow backward from the turbine side through the air flow resistance component 200 to the compressor side. When the high-temperature gas at the turbine undergoes backflow, the gas can pass through the second transfer pipeline 220 from the turbine side and flow into the flow resistance ring 100. The gas flows from the tail end to the head end of the flow resistance ring sleeve 110. The gas forms eddies between the multiple flow resistance plates 120, and the resistance received increases. The pressure of the gas flowing from the tail end to the head end of the flow resistance ring sleeve 110 decreases, which can effectively prevent the backflow of high-temperature gas and avoid damage to the engine 300 by high-temperature gas, ensuring the safety of the engine.

[0042] In some embodiments, as Figure 6 shown, the engine 300 may further include: a first transfer flange 311, arranged on the outer side of the engine housing 310, communicating with the engine housing 310, located on the compressor side, and connected to the second end of the first transfer pipeline 210. A first ventilation opening may be provided at the engine housing 310 on the compressor side. The first transfer flange 311 is fixedly arranged at the first ventilation opening, and the first transfer flange 311 is fixedly connected to the second end of the first transfer pipeline 210 of the air flow resistance component 200. A second transfer flange 312, arranged on the outer surface of the engine housing 310, communicating with the engine housing 310, located on the turbine side, and connected to the second end of the second transfer pipeline 220. A second ventilation opening may be provided at the engine housing 310 on the turbine side. The second transfer flange 312 is fixedly arranged at the second ventilation opening, and the second transfer flange 312 is fixedly connected to the second end of the second transfer pipeline 220 of the air flow resistance component 200.

[0043] Based on the same inventive concept, the present disclosure also provides a manufacturing method for an air flow resistance component 200 for an engine according to any of the foregoing embodiments, which may include:

[0044] Obtain the gas pressure loss of the flow resistance ring sleeve 110 from the tail end to the head end. When the gas flows from the tail end to the head end of the flow resistance ring sleeve 110, vortices are formed between multiple flow resistance plates 120, and the resistance received increases, resulting in gas pressure loss when the gas flows from the tail end to the head end of the flow resistance ring sleeve 110. The gas pressure losses of the flow resistance rings 100 with various different configurations at different gas flow rates and air pressures can be obtained through testing; the gas pressure loss data can also be obtained by querying the pressure loss data table of the flow resistance ring 100; the gas pressure loss of the flow resistance ring 100 can also be obtained through theoretical calculation.

[0045] Obtain the pressure difference between the maximum pressure on the turbine side and the minimum pressure on the compressor side when the engine 300 is in the working state. When the engine 300 is working, the air pressure of the high-temperature gas on the turbine side increases. When the air pressure on the turbine side is greater than the air pressure on the compressor side, gas flow is generated by the pressure, and the high-temperature gas in the turbine will produce backflow; the pressure difference can be obtained through the standard parameter information of the engine 300, or pressure sensors can be set at the first flange interface 130 and the second flange interface 140 to obtain the real-time pressure difference during operation.

[0046] Based on the gas pressure loss value and the pressure difference, determine one flow resistance ring 100 or multiple flow resistance rings 100 connected end to end, where the total gas pressure loss of one flow resistance ring 100 or multiple flow resistance rings 100 connected end to end is greater than or equal to the pressure difference. When the gas backflows from the turbine side to the engine 300 side, the pressure difference causes the gas to backflow. By setting one flow resistance ring 100 or multiple flow resistance rings 100 connected end to end, such that the pressure loss of the backflow gas and the total gas pressure loss are greater than or equal to the pressure difference, gas backflow can be avoided.

[0047] Connect one flow resistance ring 100 or multiple flow resistance rings 100 connected end to end to the first transfer pipeline 210 and the second transfer pipeline 220; the first transfer pipeline 210, one flow resistance ring 100 or multiple flow resistance rings 100 connected end to end, the first transfer pipeline 210, and the second transfer pipeline 220 can be connected in sequence to obtain the air flow resistance assembly 200; a connecting pipeline can also be installed, and the connecting pipeline can be provided between the first transfer pipeline 210 and the flow resistance ring 100, or can be provided between the second transfer pipeline 220 and the flow resistance ring 100. When there are multiple flow resistance rings 100, the connecting pipeline can be provided between multiple flow resistance rings 100.

[0048] In some embodiments, determining one flow resistance ring 100 or multiple flow resistance rings 100 connected end to end based on the gas pressure loss value and the pressure difference may include: the total gas pressure loss of one flow resistance ring 100 or multiple flow resistance rings 100 connected end to end is greater than or equal to the pressure difference and less than or equal to a first threshold. The first threshold may be the total gas pressure loss that ensures the air circulation within one flow resistance ring 100 or multiple flow resistance rings 100 connected end to end when the gas flows from the compressor side to the turbine side. Due to the funnel-shaped structure of the flow resistance plate 120, certain eddies may also be generated when the gas flows from the compressor side to the turbine side, resulting in resistance to the gas flowing from the compressor side to the turbine side. When the total gas pressure loss is greater than the first threshold, the gas flowing from the compressor side to the turbine side is resisted and the forward circulation is blocked; when the total gas pressure loss is less than or equal to the first threshold, the gas flowing from the compressor side to the turbine side can flow forward.

[0049] This application uses specific terms to describe the embodiments of this application. For example, "one embodiment", "an embodiment", and / or "some embodiments" mean a certain feature, structure, or characteristic related to at least one embodiment of this application. Therefore, it should be emphasized and noted that the "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more at different positions in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.

[0050] In the context of this application, unless the context clearly indicates an exception, words such as "a", "an", "one", and / or "the" are not specifically singular and may also include the plural. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of the clearly identified steps and elements, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0051] Similarly, it should be noted that, in order to simplify the description of this application and thus help the understanding of one or more application embodiments, in the previous description of the embodiments of this application, sometimes multiple features are merged into one embodiment, drawing, or description thereof. However, this disclosure method does not mean that the features required by the object of this application are more than those mentioned in the claims. In fact, the features of the embodiment are fewer than all the features of the single embodiment disclosed above.

[0052] The basic concepts have been described above. Obviously, for those skilled in the art, the above disclosure is only an example and does not constitute a limitation to this application. Although not explicitly stated here, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are proposed in this application, so such modifications, improvements, and corrections still fall within the spirit and scope of the embodiments of this application.

Claims

1. A flow resistance ring, wherein: The flow resistance ring comprises: A flow resistance ring sleeve, which is a hollow pipe for gas circulation, and includes a head end and a tail end along the axial direction; A plurality of flow resistance plates are arranged on the inner side of the flow resistance ring along the axial direction of the flow resistance ring; the flow resistance plate is funnel-shaped, having a wide end and a narrow end, the wide end is fixedly arranged on the inner surface of the flow resistance ring, the flow resistance plate extends radially inwardly along the flow resistance ring and extends axially toward the tail end of the flow resistance ring to form the narrow end for gas to pass through; the gas entering from the tail end forms a vortex between the plurality of flow resistance plates to reduce the pressure of the gas discharged from the head end.

2. The flow resistance ring according to claim 1, wherein: The flow resistance ring also includes: a first flange interface and a second flange interface; The first flange interface is located at the head end of the flow resistance ring and can be connected to the second flange interface of another flow resistance ring; The second flange interface is located at the rear end of the flow resistance ring and can be connected to the first flange interface of another flow resistance ring.

3. The flow resistance ring according to claim 1, wherein: The material of the flow resistance plate is shape memory alloy; when the temperature of the gas in the flow resistance ring is greater than or equal to the temperature threshold, the opening area of ​​the narrow end of the flow resistance plate becomes smaller.

4. The flow resistance ring according to claim 1, wherein: The included angle between the flow resistance plate and the inner wall of the flow resistance ring sleeve is greater than or equal to 30 degrees and less than or equal to 60 degrees.

5. An air flow resistance assembly for an engine, wherein: The air flow resistance component comprises: A flow resistance ring as claimed in any one of claims 1 to 4 or a plurality of flow resistance rings as claimed in any one of claims 1 to 4 connected end to end; A first transfer pipe is a hollow pipe, a first end of the first transfer pipe is connected to the head end of the flow resistance ring, and a second end of the first transfer pipe is used to communicate with the compressor of the engine; A second transfer pipe is a hollow pipe, a first end of the second transfer pipe is connected to the tail end of the flow resistance ring, and a second end of the second transfer pipe is used to communicate with the turbine of the engine; The gas entering the flow resistance ring from the turbine through the second transfer pipe from the tail end of the flow resistance ring sleeve forms a vortex between the multiple flow resistance plates to reduce the pressure of the gas discharged from the head end.

6. The air flow resistance assembly for an engine according to claim 5, wherein: The air flow resistance assembly also includes: a sealing member; the sealing member is arranged at the head end and the tail end of the flow resistance ring and is used for sealing to prevent gas from escaping.

7. The air flow resistance assembly for an engine according to claim 5, wherein: The air flow resistance assembly further includes: a clamp; the clamp is sleeved on the head end and the tail end of the flow resistance ring and is used to fix the flow resistance ring and the transfer pipe.

8. An engine, wherein: The engine comprises: An air flow resistance assembly for an engine as claimed in any one of claims 5 to 7; An engine casing, wherein a combustion chamber is provided inside the engine casing, a compressor is provided on a first side of the combustion chamber, and a turbine is provided on a second side of the combustion chamber; the air flow resistance component is provided on the outside of the engine casing, the compressor side of the engine casing is connected to the second end of the first transfer pipe of the air flow resistance component; the turbine side of the engine casing is connected to the second end of the second transfer pipe of the air flow resistance component; gas can flow from the compressor side to the turbine side through the air flow resistance component; gas can pass through the air flow resistance component from the turbine side to form a vortex between the multiple flow resistance plates to reduce the pressure of the gas discharged from the compressor side.

9. The engine according to claim 8, wherein: The engine also includes: A first transfer flange is provided on the outside of the engine casing, communicated with the engine casing, located on one side of the compressor, and connected to the second end of the first transfer pipe; The second adapter flange is arranged on the outer surface of the engine casing, communicated with the engine casing, located on one side of the turbine, and connected to the second end of the second adapter pipe.

10. A method for manufacturing an air flow resistance component for an engine according to any one of claims 5 to 7, comprising: Obtain the gas pressure loss from the tail end to the head end of the flow resistance ring; Obtain the pressure difference between the maximum pressure on the turbine side and the minimum pressure on the compressor side when the engine is in working condition; Based on the gas pressure loss value and the pressure difference, determining a flow resistance ring or a plurality of flow resistance rings connected end to end, wherein the sum of the gas pressure losses of the flow resistance ring or the plurality of flow resistance rings connected end to end is greater than or equal to the pressure difference; The one flow resistance ring or a plurality of flow resistance rings connected end to end are connected to the first transfer tube and the second transfer tube.

11. The method for manufacturing an air flow resistance component for an engine according to claim 10, wherein: The determining of a flow resistance ring or multiple flow resistance rings connected end to end based on the gas pressure loss value and the pressure difference includes: the sum of the gas pressure losses of the flow resistance ring or the multiple flow resistance rings connected end to end is greater than or equal to the pressure difference, and less than or equal to a first threshold.

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