Heat exchange compensation integrated device, power components and launching device

Abstract

This invention relates to the field of aerospace launch technology, and provides a heat exchange compensation integrated device, a power assembly, and a launch device. The heat exchange compensation integrated device includes a compensator body and heat exchange piping. The compensator body is connected to the turbine exhaust pipe of the engine. The compensator body has a venting cavity, which is interconnected with the turbine exhaust pipe. The heat exchange piping is arranged within the venting cavity of the compensator body. With this structural arrangement, the high-temperature exhaust gas discharged from the turbine exhaust pipe flows through the venting cavity of the compensator body and exchanges heat with the propellant flowing through the heat exchange piping. This reduces the space occupied by the heat exchange compensation integrated device, thereby reducing the volume of the engine gas inlet structure and the heat exchange structure, and improving the effective payload capacity of the launch device.

Description

Technical Field

[0001] This invention relates to the field of aerospace engine technology, and in particular to a heat exchange compensation integrated device, a power component, and a launch device. Background Technology

[0002] The second-stage engine of a liquid rocket is the main propulsion unit, and its mass and performance play a decisive role in the rocket's payload capacity. To reduce energy loss and increase the engine's specific impulse, a gas inlet system is typically employed, where turbine exhaust gas is introduced into the extended section of the engine nozzle for afterburner combustion, while simultaneously providing excellent film cooling to the nozzle's inner wall. This system requires a heat exchanger and a gas compensator to be installed on the limited length of the turbine exhaust pipe. The heat exchanger is used for pressurizing the second-stage propellant tank, and the gas compensator is used for structural compensation between the turbine exhaust duct and the thrust chamber nozzle. In existing technologies, the heat exchanger and gas compensator are usually installed independently in series, which occupies a large space, increasing the rocket's volume and affecting its effective payload capacity. Summary of the Invention

[0003] This invention provides a heat exchange compensation integrated device, a power component, and a launch device to solve the problem in the prior art where the heat exchanger and the gas compensator are set up independently in series, which occupies a large space, increases the size of the rocket, and affects the effective carrying capacity of the rocket launch.

[0004] According to a first aspect of the present invention, a heat exchange compensation integrated device is provided, comprising a compensator body and heat exchange pipelines.

[0005] The compensator body is used to connect to the turbine exhaust pipe of the engine. The compensator body has a venting cavity. The venting cavity of the compensator body is interconnected with the turbine exhaust pipe. The heat exchange pipe is laid in the venting cavity of the compensator body.

[0006] According to the integrated heat exchange compensation device provided by the present invention, an inner liner cylinder is provided on the inner side of the compensator body. The outer wall of the inner liner cylinder is welded to the inner wall of the compensator body.

[0007] According to the present invention, a heat exchange compensation integrated device is provided, wherein the heat exchange pipeline is arranged in the inner cavity of the inner liner cylinder. The inner cavity of the inner liner cylinder is interconnected with the turbine exhaust pipeline.

[0008] According to the present invention, a heat exchange compensation integrated device is provided, wherein the compensator body is a bellows. One end of the bellows is connected to the end of the exhaust pipe of the engine. A guide plate is provided at the end of the exhaust pipe of the engine. The guide plate extends toward the inner cavity of the inner liner cylinder to guide the airflow into the inner cavity of the inner liner cylinder.

[0009] According to the present invention, a heat exchange compensation integrated device is provided, wherein the heat exchange pipeline is a spiral tube. The spiral tube is arranged along a direction parallel to the central axis of the inner liner cylinder.

[0010] According to a heat exchange compensation integrated device provided by the present invention, the heat exchange compensation integrated device further includes an input pipeline and an output pipeline. One end of the input pipeline is connected to the inlet end of the heat exchange pipeline, and the other end of the input pipeline passes through the side wall of the turbine exhaust pipeline of the engine and extends to the outside of the turbine exhaust pipeline of the engine. An inlet flange is installed at the other end of the input pipeline. One end of the output pipeline is connected to the outlet end of the heat exchange pipeline, and the other end of the output pipeline passes through the side wall of the turbine exhaust pipeline of the engine and extends to the outside of the turbine exhaust pipeline of the engine. An outlet flange is installed at the other end of the output pipeline.

[0011] According to the integrated heat exchange compensation device provided by the present invention, the corrugated pipe is an elastic corrugated pipe structure, and the inner lining cylinder is a rigid cylinder structure.

[0012] According to a second aspect of the present invention, a power assembly is provided, including an engine and a heat exchange compensation integrated device as described above. The engine is provided with a turbine exhaust pipe. The heat exchange compensation integrated device is connected to the turbine exhaust pipe.

[0013] According to a third aspect of the invention, a launching device is also provided, comprising the heat exchange compensation integrated device or power component as described above.

[0014] The heat exchange compensation integrated device provided by this invention includes a compensator body and heat exchange piping. The compensator body is connected to the turbine exhaust pipe of the engine. The compensator body has axial, radial, and tangential displacement compensation capabilities to compensate for deformations caused during engine operation and turbopump assembly. The compensator body has a venting cavity, which is interconnected with the turbine exhaust pipe. High-temperature exhaust gases discharged from the turbine exhaust pipe can flow through the venting cavity of the compensator body. The heat exchange piping is laid into the venting cavity of the compensator body, and propellant flows through the heat exchange piping. The propellant flowing through the heat exchange piping can exchange heat with the high-temperature exhaust gases in the venting cavity of the compensator body.

[0015] This structural design integrates heat exchange piping into the ventilation cavity of the compensator body. High-temperature exhaust gases from the turbine exhaust pipe flow through this cavity and exchange heat with the propellant flowing through the heat exchange piping. This reduces the space occupied by the integrated heat exchange compensation device, thereby reducing the volume of the engine gas inlet structure and the heat exchange structure, and improving the effective payload capacity of the launch vehicle.

[0016] Furthermore, since both the power assembly and the launching device provided by the present invention include the heat exchange compensation integrated device as described above, they also possess the advantages described above. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the integrated heat exchange compensation device provided by the present invention.

[0019] Reference numerals: 100, compensator body; 200, heat exchange pipeline; 300, turbine exhaust pipeline; 400, inner liner; 500, guide plate; 700, input pipeline; 710, inlet flange; 600, output pipeline; 610, outlet flange. Detailed Implementation

[0020] The embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and should not be construed as limiting the scope of the invention.

[0021] In the description of the embodiments of the present invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0022] In the description of the embodiments of the present invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of the present invention based on the specific circumstances.

[0023] In embodiments of the present invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0024] In the description of this specification, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Furthermore, without contradiction, those skilled in the art can combine and integrate different embodiments or examples and features of different embodiments or examples described in this specification to make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer. The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] The following is combined with Figure 1 This invention describes an integrated heat exchange compensation device, a power assembly, and a launching device provided in an embodiment of the invention. It should be understood that the following description is merely an illustrative embodiment of the invention and does not constitute any particular limitation on the invention.

[0026] An embodiment of the first aspect of the present invention provides a heat exchange compensation integrated device, such as... Figure 1 As shown, the heat exchange compensation integrated device includes a compensator body 100 and a heat exchange pipeline 200.

[0027] The compensator body 100 is used to connect to the turbine exhaust pipe 300 of the engine. The compensator body 100 has a venting cavity. The venting cavity of the compensator body 100 is interconnected with the turbine exhaust pipe 300. The heat exchange pipe 200 is arranged in the venting cavity of the compensator body 100.

[0028] The heat exchange compensation integrated device provided by this invention includes a compensator body 100 and a heat exchange pipeline 200. The compensator body 100 is connected to the turbine exhaust pipeline 300 of the engine. The compensator body 100 has axial, radial, and tangential displacement compensation capabilities to compensate for deformations caused during engine operation and turbopump assembly. The compensator body 100 has a venting cavity, which is interconnected with the turbine exhaust pipeline 300. High-temperature exhaust gases discharged from the turbine exhaust pipeline 300 can flow through the venting cavity of the compensator body 100. The heat exchange pipeline 200 is arranged in the venting cavity of the compensator body 100, and propellant flows through the heat exchange pipeline 200. The propellant flowing through the heat exchange pipeline 200 can exchange heat with the high-temperature exhaust gases in the venting cavity of the compensator body 100.

[0029] With this structural arrangement, the heat exchange pipe 200 is laid into the ventilation cavity of the compensator body 100. The high-temperature exhaust gas discharged from the turbine exhaust pipe 300 flows through the ventilation cavity of the compensator body 100 and exchanges heat with the propellant flowing through the heat exchange pipe 200. This reduces the space occupied by the integrated heat exchange compensation device, thereby reducing the volume of the engine gas inlet structure and the heat exchange structure, and improving the effective payload capacity of the launch vehicle.

[0030] In one embodiment of the present invention, an inner liner 400 is provided on the inner side of the compensator body 100. The outer wall of the inner liner 400 is welded to the inner wall of the compensator body 100.

[0031] In one embodiment of the present invention, the heat exchange pipe 200 is arranged in the inner cavity of the inner liner cylinder 400. The inner cavity of the inner liner cylinder 400 is interconnected with the turbine exhaust pipe 300.

[0032] In one embodiment of the present invention, the compensator body 100 is a bellows. One end of the bellows is connected to the end of the engine's exhaust pipe. A guide plate 500 is provided at the end of the engine's exhaust pipe. The guide plate 500 extends toward the inner cavity of the inner liner 400 to guide airflow into the inner cavity of the inner liner 400.

[0033] In another embodiment of the present invention, the bellows is an elastic bellows structure, and the inner lining cylinder 400 is a rigid cylinder structure.

[0034] For example, such as Figure 1As shown, the compensator body 100 is an elastic bellows, and the inner liner 400 is a rigid cylindrical structure. In the illustrated direction, the left end of the elastic bellows is connected to the right end of the turbine exhaust pipe 300. The inner liner 400 is fitted inside the elastic bellows, and the outer wall of the inner liner 400 is as close as possible to the small-diameter inner wall of the elastic bellows. The turbine exhaust pipe 300, the elastic bellows, and the rigid inner liner 400 are coaxially arranged. The heat exchange pipe 200 is arranged inside the inner cavity of the inner liner 400. Thus, the high-temperature exhaust gas discharged from the turbine exhaust pipe 300 can flow through the inner cavity of the inner liner 400. The propellant flowing through the heat exchange pipe 200 can exchange heat with the high-temperature exhaust gas inside the inner cavity of the inner liner 400. By setting the inner liner 400 inside the elastic bellows, not only can a certain deformation compensation capability be provided, but the flowability of the high-temperature exhaust gas can also be improved. In addition, a guide vane 500 is provided at the right end of the turbine exhaust pipe 300 of the engine. One end of the guide vane 500 is connected to the end of the turbine exhaust pipe 300, and the other end of the guide vane extends into the inner cavity of the inner liner cylinder 400. This allows the high-temperature exhaust gas discharged from the turbine exhaust pipe 300 to be discharged into the inner cavity of the inner liner cylinder 400 as much as possible.

[0035] In one embodiment of the present invention, such as Figure 1 As shown, the heat exchange pipe 200 is a spiral pipe, which is arranged along a direction parallel to the central axis of the inner liner cylinder 400. This allows for maximizing the heat exchange path of the heat exchange pipe 200 within the limited space of the inner liner cylinder 400, thereby improving the heat exchange effect of the propellant.

[0036] In one embodiment of the present invention, such as Figure 1 As shown, the heat exchange compensation integrated device also includes an input pipe 700 and an output pipe 600. One end of the input pipe 700 is connected to the inlet end of the heat exchange pipe 200, and the other end of the input pipe 700 passes through the side wall of the engine's turbine exhaust pipe 300 and extends to the outside of the engine's turbine exhaust pipe 300. An inlet flange 710 is installed at the other end of the input pipe 700. One end of the output pipe 600 is connected to the outlet end of the heat exchange pipe 200, and the other end of the output pipe 600 passes through the side wall of the engine's turbine exhaust pipe 300 and extends to the outside of the engine's turbine exhaust pipe 300. An outlet flange 610 is installed at the other end of the output pipe 600. The inlet flange 710 is connected to the propellant supply end, and the outlet flange 610 is connected to the pressurization tank.

[0037] A second aspect of the present invention provides a power assembly including an engine and a heat exchange compensation integrated device as described above. A turbine exhaust pipe 300 is provided on the engine. The heat exchange compensation integrated device is connected to the turbine exhaust pipe 300.

[0038] A third aspect of the present invention provides a launching device, including the heat exchange compensation integrated device or power component as described above.

[0039] For example, in one embodiment of the present invention, the launching device is a rocket.

[0040] Furthermore, since both the power assembly and the launching device provided by the present invention include the heat exchange compensation integrated device as described above, they also possess the advantages described above.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A heat exchange compensation integrated device, characterized in that, Includes the compensator body (100) and heat exchange pipeline (200). The compensator body (100) is used to connect to the turbine exhaust pipe (300) of the engine. The compensator body (100) has a ventilation cavity. The ventilation cavity of the compensator body (100) is interconnected with the turbine exhaust pipe (300). The heat exchange pipe (200) is arranged in the ventilation cavity of the compensator body (100). The compensator body (100) is provided with an inner liner cylinder (400) on its inner side, and the outer wall of the inner liner cylinder (400) is welded to the inner wall of the compensator body (100). The heat exchange pipeline (200) is laid into the inner cavity of the inner liner cylinder (400), and the inner cavity of the inner liner cylinder (400) is connected to the turbine exhaust pipeline (300). The compensator body (100) is a bellows, one end of which is connected to the exhaust pipe end of the engine. The exhaust pipe end of the engine is provided with a guide plate (500), which extends toward the inner cavity of the inner liner cylinder (400) to guide the flow into the inner cavity of the inner liner cylinder (400). The heat exchange pipeline (200) is a spiral tube, which is arranged along a direction parallel to the central axis of the inner liner cylinder (400).

2. The heat exchange compensation integrated device according to claim 1, characterized in that, The heat exchange compensation integrated device further includes an input pipe (700) and an output pipe (600). One end of the input pipe (700) is connected to the inlet end of the heat exchange pipe (200), and the other end of the input pipe (700) passes through the inside of the turbine exhaust pipe (300) of the engine, through the side wall of the turbine exhaust pipe (300), and extends to the outside of the turbine exhaust pipe (300). An inlet flange (710) is installed at the other end of the input pipe (700). One end of the output pipe (600) is connected to the outlet end of the heat exchange pipe (200), and the other end of the output pipe (600) passes through the inside of the turbine exhaust pipe (300) of the engine, through the side wall of the turbine exhaust pipe (300), and extends to the outside of the turbine exhaust pipe (300). An outlet flange (610) is installed at the other end of the output pipe (600).

3. The heat exchange compensation integrated device according to claim 1, characterized in that, The corrugated pipe is an elastic corrugated pipe structure, and the inner lining cylinder (400) is a rigid cylinder structure.

4. A power assembly, characterized in that, The device includes an engine and a heat exchange compensation integrated device as described in any one of claims 1 to 3, wherein the engine is provided with a turbine exhaust pipe (300) and the heat exchange compensation integrated device is connected to the turbine exhaust pipe (300).

5. A launching device, characterized in that, Includes the heat exchange compensation integrated device as described in any one of claims 1 to 3.

6. A launching device, characterized in that, Includes the power assembly as described in claim 4.

Images