CN210509426U

CN210509426U - Liquid rocket engine thrust chamber cooling structure, thrust chamber and liquid rocket

Info

Publication number: CN210509426U
Application number: CN201921157918.1U
Authority: CN
Inventors: 袁宇; 宣智超; 杨瑞康; 韩建业
Original assignee: Landspace Technology Co Ltd
Current assignee: Zhejiang Landspace Technology Co Ltd
Priority date: 2019-07-23
Filing date: 2019-07-23
Publication date: 2020-05-12
Anticipated expiration: 2029-07-23

Abstract

The utility model discloses a liquid rocket engine thrust chamber cooling structure, a thrust chamber and a liquid rocket, wherein the thrust chamber cooling structure comprises a coolant inlet channel, an outer pipeline, a first collector, a second collector and a coolant channel; coolant inlet channel divide into first export and second export, and first export is connected through outer pipeline first collector, first collector setting in thrust room main aspects and be close to the outside of tip to link to each other with the entrance of coolant liquid passageway at thrust room main aspects, second collector respectively with second export and coolant liquid channel connection, coolant liquid partly warp first export outer pipeline first collector gets into the coolant liquid passageway, meets with another part coolant liquid that gets into the coolant liquid passageway through the second export, flows in thrust room tip along the coolant liquid passageway, compares with prior art, the utility model discloses a thrust room cooling structure reasonable in design, stable in structure, the control of being convenient for, safe and reliable.

Description

Liquid rocket engine thrust chamber cooling structure, thrust chamber and liquid rocket

Technical Field

The utility model relates to a liquid rocket field, in particular to liquid rocket engine thrust chamber cooling structure, thrust chamber and liquid rocket.

Background

With the rapid development of the aerospace industry, various technologies related to rockets also realize the rapid advance. Currently, the continuous reduction of rocket manufacturing and launch costs as the only vehicle currently launching satellites into space is a pursuit goal of large commercial space companies.

The thrust chamber of the rocket engine mainly plays a role in organizing combustion and generating thrust, and the combustion chamber needs to be reliably cooled to ensure that the structure is not damaged by fuel gas due to the fact that the temperature of the fuel gas is very high (more than 3000 ℃). At present, the mainstream cooling structure of the thrust chamber of the rocket engine adopts a regenerative cooling mode of a sandwich structure on the shell of the body part of the thrust chamber. Namely, the coolant passes through the inlet, one part of the coolant enters the sandwich structure through the shunt pipeline and then flows to the large end of the thrust chamber, then enters the collector, the coolant passing through the collector flows back to the small end of the thrust chamber through the outer pipe, the other part of the coolant flows into the small end of the thrust chamber through the sandwich structure, the convergence of the two paths of the coolant is realized at the small end of the thrust chamber, and the cooling of the thrust chamber is further completed.

By adopting the cooling mode, the flow dividing proportion of the coolant cannot be changed after the processing is finished, so that the requirement on the consistency of products is high. If the flow distribution ratio is not ideal after the liquid flow test, the product cannot be repaired, and a larger scrapping risk exists.

Therefore, how to provide a cooling structure of a thrust chamber of a liquid rocket engine, which has the advantages of reasonable design, stable structure, convenient control, safety and reliability and can save energy is the problem to be solved at present.

Disclosure of Invention

The utility model aims at providing a liquid rocket engine thrust chamber cooling structure has reasonable in design, stable in structure, the control of being convenient for, safe and reliable can advantages such as energy saving simultaneously.

In order to achieve the above object, the utility model provides a following technical scheme: a liquid rocket engine thrust chamber cooling structure comprises a coolant inlet channel, an outer pipeline, a first collector, a second collector and a coolant channel; the coolant inlet channel is divided into a first outlet positioned at the upstream and a second outlet positioned at the downstream, the first outlet is connected with the first collector through the outer pipeline, the first collector is arranged at the large end of the thrust chamber and close to the outer side of the end part and is connected with the inlet of the coolant channel at the large end of the thrust chamber, the second collector is respectively connected with the second outlet and the coolant channel, and the second outlet is positioned at the part of the coolant channel between the large end of the thrust chamber and the throat part of the thrust chamber; a part of the cooling liquid enters the cooling liquid channel through the first outlet, the outer pipeline and the first collector, meets another part of the cooling liquid entering the cooling liquid channel through the second outlet, and flows into the small end of the thrust chamber along the cooling liquid channel.

Preferably, a throttling device is arranged on the coolant inlet channel and is positioned between the first outlet and the second outlet.

Preferably, the throttling device is an orifice plate, and the orifice plate is used for regulating the flow rate of the cooling liquid entering the second collector.

Preferably, the second outlet is located between the thrust chamber throat and one half of the distance between the thrust chamber large end and the thrust chamber throat.

Preferably, the second outlet is located between one quarter and one half of the way from the throat of the thrust chamber.

Preferably, an injector is arranged at the small end of the thrust chamber, and the mixed cooling liquid is injected into the thrust chamber through the injector.

Preferably, the first collector comprises a pipe and a tee, and the pipe and the tee are connected through threads.

Preferably, an opening channel communicated with the cooling liquid channel is formed in one side, close to the thrust chamber, of the circular tube, so that the cooling liquid entering the first collector can conveniently flow into the cooling liquid channel.

The embodiment also provides a liquid rocket engine thrust chamber, which comprises the liquid rocket engine thrust chamber cooling structure.

The present embodiment also provides a liquid rocket including any one of the above cooling structures for a thrust chamber of a liquid rocket engine.

Compared with the prior art, the beneficial effects of the utility model are that: the liquid rocket engine thrust chamber cooling structure consists of a coolant inlet channel, an outer pipeline, a first collector, a second collector and a coolant channel; the coolant inlet channel is divided into a first outlet positioned at the upstream and a second outlet positioned at the downstream, so that the coolant can be conveniently distributed, the number of outer pipelines is reduced, the weight of the whole thrust chamber is further reduced, the first outlet is connected with the first collector through the outer pipeline, the first collector is arranged at the large end of the thrust chamber and is close to the outer side of the end part and is connected with the inlet of the coolant channel at the large end of the thrust chamber, so that the coolant can conveniently flow into the outer pipeline from the first outlet, the coolant can conveniently enter the first collector, the second collector is respectively connected with the second outlet and the coolant channel, the coolant can conveniently flow into the coolant channel after flowing into the second collector through the second outlet, and a part of the coolant can enter the coolant channel through the first outlet, the outer pipeline and the first collector, with get into through the second export another part coolant liquid of coolant liquid passageway meets, follows coolant liquid passageway flows into thrust chamber tip, because the second export is located the part of coolant liquid passageway between thrust chamber main aspects and thrust chamber throat is convenient for cool down thrust chamber surface, whole structural design is reasonable, stable in structure, and the control of being convenient for, safe and reliable can energy saving etc. advantage simultaneously.

Drawings

FIG. 1 is a half sectional view of a thrust chamber cooling structure of a conventional liquid rocket engine;

FIG. 2 is an enlarged partial view of the fuel inlet and the manifold.

FIG. 3 is a half sectional view of a thrust chamber cooling structure of a liquid rocket engine according to the present embodiment;

fig. 4 is a structural view of a thrust chamber cooling structure of a liquid rocket engine according to the present embodiment;

FIG. 5 is a left side view of a cooling structure of a thrust chamber of a liquid rocket engine according to the present embodiment;

fig. 6 is a left side view of the first collector in the present embodiment;

fig. 7 is a schematic structural view of a half round tube in the present embodiment.

Description of reference numerals:

1a oxidizer chamber 2a fuel head chamber

3a injector 4a body jacket

5a return line 6a fuel inlet

7a shunt tube 8a spray tube extension section jacket outlet collector

9a body housing 10a nozzle extension housing

11a body jacket inlet collector 12a orifice plate

13a body flange 14a nozzle extension flange

15a lance extension jacket inlet collector 16a seal ring

1 Coolant inlet channel 2 external pipe

3 first collector 4 second collector

5 first outlet of cooling liquid channel 6

7 second outlet 8 thrust chamber big end

9 small end of thrust chamber and 10 throat of thrust chamber

11 throttling means 12 injector

13 thrust chamber 14 round tube

15 tee 16 open channel

Detailed Description

To make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the spirit of the present invention will be described in detail with reference to the accompanying drawings, and any person skilled in the art can change or modify the techniques taught by the present invention without departing from the spirit and scope of the present invention after understanding the embodiments of the present invention.

The exemplary embodiments and descriptions of the present invention are provided to explain the present invention, but not to limit the present invention. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.

As used herein, the terms "first," "second," …, etc. do not denote any order or sequential importance, nor are they used to limit the invention, but rather are used to distinguish one element from another or from another element or operation described in the same technical language.

With respect to directional terminology used herein, for example: up, down, left, right, front or rear, etc., are simply directions with reference to the drawings. Accordingly, the directional terminology used is intended to be illustrative and is not intended to be limiting of the present teachings.

As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.

As used herein, "and/or" includes any and all combinations of the described items.

As used herein, the terms "substantially", "about" and the like are used to modify any slight variation in quantity or error that does not alter the nature of the variation. Generally, the range of slight variations or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. It should be understood by those skilled in the art that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.

Certain words used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the present application.

In the prior art, as shown in fig. 1 and 2, after passing through a fuel inlet, a part of cooling fluid passes through a body housing 9a, enters a body jacket 4a through a throat of a thrust chamber, and another part of the cooling fluid passes through a body jacket inlet collector 11 and then enters a shunt tube 7a, and the cooling fluid passing through the shunt tube 7a enters a nozzle extension jacket inlet collector 15a, then enters a nozzle extension housing 10, and then enters a nozzle extension jacket outlet collector 8a, and then meets the cooling fluid passing through the body housing 9a at a small end of the thrust chamber after passing through a return pipe 5a, and finally enters a fuel head chamber 2a to be mixed with an oxidant passing through an oxidant chamber 1a inside the thrust chamber through an injector 3 a.

For example, the thrust barrel body integral regenerative cooling jacket can be divided into a combustion barrel body jacket 4a and a nozzle extension jacket, which are connected to each other by a combustion barrel body flange 13a and a nozzle extension flange 14a, and the internal combustion gas is sealed by a seal ring 16 a. The low-temperature fuel enters a body jacket inlet collector 11a from a fuel inlet 6a, and most of the low-temperature fuel is distributed to enter a body jacket 4a through the body jacket inlet collector 11a and flows towards the small end of the thrust chamber; a small part of fuel enters the jacket of the extension section of the jet pipe through a shunt pipe 7a (4 pipelines can be arranged in the axial direction to ensure uniformity), flows to the large end of the thrust chamber to cool the jacket of the jet pipe, returns to the small end of the thrust chamber through an outlet collector 8a of the jacket of the extension section of the jet pipe and an outer pipeline, and is mixed with a coolant towards the small end of the thrust chamber. For example, flow into the nozzle extension may be controlled by means of an orifice plate 12 a.

The thrust chamber has the highest heat flux density near the throat portion of the thrust chamber (the bent portion of the body casing 9 a), and is the place where the cooling requirement is highest. The cooling reliability at the throat is significantly reduced by the fact that only a portion of the fuel used as the coolant flows through the throat in the cooling flow scheme and the flow rate uniformity is poor. In order to ensure the propulsion chamber to work properly, the wall thickness can be increased accordingly, but this will result in an increase in the weight of the propulsion chamber and thus in an increase in the weight of the rocket. Obviously, the method of increasing the wall thickness of the throat part of the thrust chamber not only wastes energy, but also increases the launching cost of the rocket.

Referring to fig. 3, 4 and 5, an embodiment of the present invention provides a cooling structure for a thrust chamber of a liquid rocket engine, including a coolant inlet channel 1, an outer pipe 2, a first collector 3, a second collector 4 and a coolant channel 5; the coolant inlet channel 1 comprises a first outlet 6 at the upstream and a second outlet 7 at the downstream, the first outlet 6 is connected with a first collector 3 through an external pipeline 2, the first collector 3 is arranged at the large end 8 of the thrust chamber and close to the outer side of the end part and is connected with the coolant channel 5 at the inlet of the large end 8 of the thrust chamber, the second collector 4 is respectively connected with the second outlet 7 and the coolant channel 5, and the second outlet 7 is positioned at the part of the coolant channel 5 between the large end 8 of the thrust chamber and the throat part 10 of the thrust chamber; one part of the cooling liquid enters the cooling liquid channel 5 through the first outlet 6, the outer pipeline 2 and the first collector 3, and is combined with the other part of the cooling liquid entering the cooling liquid channel 5 through the second outlet 7, and flows into the small end 9 of the thrust chamber along the cooling liquid channel 5.

Specifically, the method comprises the following steps: the liquid rocket engine thrust chamber cooling structure is composed of a coolant inlet channel 1, an outer pipeline 2, a first collector 3, a second collector 4 and a coolant channel 5. Since the coolant inlet passage 1 is divided into the first outlet 6 located upstream and the second outlet 7 located downstream, the split flow of the coolant is facilitated, while the number of outer pipes 2 is reduced, thereby reducing the weight of the entire thrust chamber 13. Because the first outlet 6 is connected with the first collector 3 through the outer pipeline 2, the first collector 3 is arranged at the large end 8 of the thrust chamber and close to the outer side of the end part, and is connected with the cooling liquid channel 5 at the inlet of the large end 8 of the thrust chamber, so that the cooling liquid can conveniently flow into the outer pipeline 2 from the first outlet 6, and the cooling liquid can conveniently enter the first collector 3. Since the second collector 4 is connected to the second outlet 7 and the cooling liquid channel 5, the cooling liquid can flow into the cooling liquid channel 5 after flowing into the second collector 4 through the second outlet 7. One part of coolant liquid is through first 6 mouths, outer pipeline 2, first collector 3 gets into coolant liquid passageway 5, with another part coolant liquid that gets into coolant liquid passageway 5 through second export 7 meets, flow into thrust chamber tip 9 along coolant liquid passageway 5, because second export 7 is located coolant liquid passageway 5 in the part between thrust chamber tip 8 and thrust chamber throat 10, can lower the temperature to the throat of thrust chamber 10 better, it is regional to the highest thrust chamber throat 10 of thermal current density, this scheme can realize that all fuels can both flow through thrust chamber throat 10 region and cool off, thereby stabilize the cooling effect of product, improve product reliability, whole structural design is reasonable, stable in structure, be convenient for control, safety and reliability, simultaneously, can advantages such as energy saving.

It should be noted that, as shown in fig. 3, for convenience of accurately controlling the flow rate of the coolant, a throttle device 11 is provided in the coolant inlet passage 1, and the throttle device 11 is provided between the first outlet 6 and the second outlet 7. It is worth mentioning that the throttling device 11 may be an orifice plate, and the orifice plate is used for adjusting the flow rate of the cooling liquid entering the first collector 3 and the second collector 4, accurately controlling the flow rate of the cooling liquid, and helping to accurately cool the surface of the thrust chamber 13. Furthermore, the orifice plate may be formed by a single large diameter orifice or a plurality of small diameter orifices, which are not illustrated here. The throttling orifice plate is an independent part, and any flow distribution proportion can be realized by assembling the throttling orifice plates with different throttling apertures. The required flow dividing proportion is achieved by replacing the throttling pore plate after the liquid flow sample, so that the requirement on the consistency of the product is relaxed.

It is further noted that in the present embodiment, for example, in order to better lower the temperature of the surface of the thrust chamber 13, the second outlet 7 is designed between the half between the end of the thrust chamber large end 8 and the thrust chamber throat 10 (for example, where the diameter of the thrust chamber throat 10 is smallest) to the thrust chamber throat 10. For example, in combustion, since the temperature of the thrust chamber throat 10 is high, in order to better reduce the temperature of the surface of the thrust chamber throat 10, it is found through many experiments that the second outlet 7 may be designed between a quarter and a half (with respect to the distance between the large end of the thrust chamber and the throat) of the thrust chamber throat 10, thereby effectively reducing the temperature of the thrust chamber throat 10.

Furthermore, as shown in fig. 3 and 4, an injector 12 is provided at the thrust chamber small end 9 in order to facilitate mixing of the coolant with the oxidant. The mixed cooling liquid is injected into a thrust chamber 13 through an injector 12.

It is particularly worth mentioning that, as shown in fig. 3, 6 and 7, in order to facilitate the entry of the cooling fluid into the cooling fluid channel 5, ensure that the first manifold 3 is tightly combined with the thrust chamber 13, and prevent the leakage of the cooling fluid, the first manifold 3 is designed to be composed of a circular tube 14 and a tee pipe, which are connected by a screw thread. It should be mentioned that, in order to rapidly deliver the coolant to the coolant channel 5, the side of the circular tube 14 near the thrust chamber 13 is provided with an open channel 16 communicating with the coolant channel 5, so as to facilitate the flow of the coolant entering the first collector 3 into the coolant channel 5.

It should be noted that the fuel in the collector in the present embodiment is all in a low temperature state and has a high density, and the structural size and the structural mass of the collector can be greatly reduced compared with the prior art. In addition, the embodiment simplifies the product structure, reduces the number of collectors, further reduces the weight of the thrust chamber, and is beneficial to the launching of the liquid rocket. In addition, in order to enable the thrust chamber body part and the spray pipe extension section to be connected more tightly, the thrust chamber body part and the spray pipe extension section can be connected through welding, the structure is reliable, and the weight of two butting flanges is saved.

It is further explained that, because fuel density is great, under the same spray tube extension cooling flow, the utility model discloses the pipe diameter and the quantity of shunt tubes also need be less than current scheme back flow, and the pipe length is also less simultaneously, when reducing structure quality, has still reduced interface welding quantity, has improved product reliability.

The present invention also relates to a second embodiment which is a replacement for a part of the elements of the first embodiment. Specifically, the throttling device in the second inlet is eliminated, and the inlet of the second inlet is provided with a throttling channel, so that the throttling function same as that of the throttling orifice plate is achieved, and the throttling function can be achieved.

The first manifold 3 is moved from the outside front (small end side) of the thrust chamber large end 8 and near the thrust chamber end to a position in the middle of the thrust chamber 13 (i.e., between the thrust chamber large end 8 end and the thrust chamber throat), and the first manifold 3 is connected to the coolant passage 5. The cooling liquid can be divided into two paths, wherein one path of cooling liquid firstly flows into the cooling liquid channel 5 at the large end 8 of the thrust chamber until the cooling liquid channel 5 at the large end of the thrust chamber is filled with the cooling liquid, and then the cooling liquid flows back along the cooling liquid channel 5 and meets the other path of cooling liquid flowing to the small end 9 of the thrust chamber through the cooling liquid channel 5.

It should be noted that a plurality of outer pipes 2 may be disposed around the thrust chamber 13, and are not limited to 1 or 2 as illustrated in the drawings. For example, the thrust chamber 13 may be provided with a plurality of outer pipes 2 uniformly arranged in the circumferential direction, one end of the outer pipes 2 being connected to the first outlet of the coolant inlet pipe and the other end being connected to the first collector 3 provided at the large-end portion of the thrust chamber.

The above embodiments may be combined with each other with corresponding technical effects.

The embodiment also provides a liquid rocket engine thrust chamber, which comprises the novel liquid rocket engine thrust chamber cooling structure.

The embodiment also provides a liquid rocket, which comprises the novel liquid rocket engine thrust chamber cooling structure.

The foregoing is only an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principles of the present invention should fall within the protection scope of the present invention.

Claims

1. The utility model provides a liquid rocket engine thrust chamber cooling structure which characterized in that: comprises a coolant inlet channel, an outer pipeline, a first collector, a second collector and a coolant channel; the coolant inlet channel is divided into a first outlet positioned at the upstream and a second outlet positioned at the downstream, the first outlet is connected with the first collector through the outer pipeline, the first collector is arranged at the large end of the thrust chamber and close to the outer side of the end part and is connected with the inlet of the coolant channel at the large end of the thrust chamber, the second collector is respectively connected with the second outlet and the coolant channel, and the second outlet is positioned at the part of the coolant channel between the large end of the thrust chamber and the throat part of the thrust chamber; a part of the cooling liquid enters the cooling liquid channel through the first outlet, the outer pipeline and the first collector, meets another part of the cooling liquid entering the cooling liquid channel through the second outlet, and flows into the small end of the thrust chamber along the cooling liquid channel.

2. The liquid rocket engine thrust chamber cooling structure of claim 1, wherein: and a throttling device is arranged on the coolant inlet channel and is positioned between the first outlet and the second outlet.

3. The liquid rocket engine thrust chamber cooling structure of claim 2, wherein: the throttling device is a throttling orifice plate which is used for adjusting the flow of the cooling liquid entering the second collector.

4. The liquid rocket engine thrust chamber cooling structure of claim 1, wherein: the second outlet is located between the half between the thrust chamber large end and the thrust chamber throat to the thrust chamber throat.

5. The liquid rocket engine thrust chamber cooling structure of claim 4, wherein: the second outlet is located between one quarter and one half of the way from the throat of the thrust chamber.

6. The liquid rocket engine thrust chamber cooling structure of claim 1, wherein: and an injector is arranged at the small end of the thrust chamber, and the mixed cooling liquid is injected into the thrust chamber through the injector.

7. The liquid rocket engine thrust chamber cooling structure of claim 1, wherein: the first collector comprises a circular pipe and a three-way pipe which are connected through threads.

8. The liquid rocket engine thrust chamber cooling structure of claim 7, wherein: the circular tube is provided with an opening channel communicated with the cooling liquid channel on one side close to the thrust chamber, so that the cooling liquid entering the first collector conveniently flows into the cooling liquid channel.

9. A liquid rocket engine thrust chamber, characterized by: including a liquid rocket engine thrust chamber cooling structure as defined in any one of claims 1-8.

10. A liquid rocket, comprising: including a liquid rocket engine thrust chamber cooling structure as defined in any one of claims 1-8.