RU2774754C1 - Liquid-propellant rocket engine chamber - Google Patents

Abstract

FIELD: rocket technology.

SUBSTANCE: invention relates to rocket technology. A chamber of a liquid-propellant rocket engine containing a combustion chamber equipped with a cooling path with longitudinal channels with transverse bridges, an inlet manifold for supplying the missing component in the gas generator with a minimum cross section towards the nozzle exit, and an outlet manifold located at the mixing head and connected by a pipeline to the inlet manifold cooling path with longitudinal channels and transverse bridges of the nozzle, by the outlet manifold of the cooling path of the latter connected by a pipeline with a mixing head, while the sections of the transverse jumpers in the interface zone of the inlet manifolds of the nozzle and the combustion chamber are discontinuous and placed alternately between the longitudinal channels in the circumferential direction, the inlet manifold of the nozzle is located between the minimum section of the nozzle and the inlet manifold of the cooling path combustion chambers, and the longitudinal channels of the cooling paths of the combustion chamber and nozzle in the interface zone with the inlet manifolds are connected at the transverse jumpers alternately by radial channels with the same inlet manifolds. The walls of the discontinuous transverse jumpers in the zone of conjugation of the inlet manifolds in the radial direction are made of a V-shaped profile and are oriented with their vertices in the directions opposite from the radial channels.

EFFECT: invention provides a reduction in the hydraulic resistance of the cooling path by reducing the temperature of the nozzle in the area of ​​the transverse bridges and reducing the temperature unevenness of the nozzle wall and the combustion chamber, as well as reducing the inlet pressure of the fuel at the inlet to the cooling path and reducing the weight of the nozzle and chamber.

2 cl, 5 dwg

Description

The invention relates to rocket technology, in which the creation of chambers of liquid rocket engines intended for installation in the compartments of the propulsion systems of the upper stages with chambers of large expansion ratios is an urgent task.

Known chambers of liquid rocket engines, containing a combustion chamber equipped with a cooling path with longitudinal channels with transverse jumpers, an input manifold for the component behind a minimum cross section towards the nozzle exit and an output manifold located at the mixing head and connected by a pipeline to the mixing head (book: "Dobrovolsky M.V. Fundamentals of the design of liquid rocket engines, Textbook for universities, - 2nd ed., revised and supplemented / edited by D.A. Yagodnikov, -M., Bauman Moscow State Technical University Publishing House , 2005. P. 149, Fig. 4.3).

In such a chamber of a liquid rocket engine, due to the non-optimal use of the coolant, when the coolant is supplied to the manifold at the outlet section of the nozzle, and then to the most heat-stressed section of the cooling path in the minimum section of the nozzle is supplied after cooling the outlet section of the nozzle with an increased temperature, it is necessary to minimize the flow area of the cooling path to achieve a high speed of the coolant, usually fuel, which leads to the need to increase the pressure at the inlet to the cooling path of the outlet section of the nozzle, due to which it is necessary to increase the thickness of the walls and ribs of the cooling path to increase strength with an increase in the mass of the outlet section of the nozzle.

Also known is a chamber of a liquid-propellant rocket engine, containing a combustion chamber equipped with a cooling path with longitudinal channels with transverse jumpers, an inlet for supplying the missing component in the gas generator by a manifold with a minimum cross section towards the nozzle exit and an outlet manifold located at the mixing head and connected by a pipeline to the inlet manifold cooling path with longitudinal channels and transverse jumpers of the nozzle, the outlet manifold of the cooling path of the latter connected by a pipeline with a mixing head (description of the patent of the Russian Federation 2556091 dated 10.06.2014, IPC F02K 9/42, Fig. 1-3 on pages 9, 10 and 11, respectively - the prototype).

In such a chamber of a liquid-propellant rocket engine, the component missing in the gas generator, fuel, is supplied to the cooling path of the minimum section of the nozzle with a reduced temperature immediately after the pump, providing cooling of the nozzle wall in the minimum section. However, the junction of the walls of the cooling paths at the place of the sequential location of two collectors of the nozzle and the combustion chamber connected by a common housing is problematic, since the relatively rigid assembly of the two input manifolds during vacuum soldering of the inner finned wall with the outer housing prevents sufficient pressing of the cooled wall with the housing, prevents high-quality soldering , there are problems with the use of chambers with increased fuel pressure in the cooling path and, consequently, combustion products in the combustion chamber. Poor-quality soldering of the ribs due to insufficient pressing of the milled wall and the body in this place is usually detected at an early stage of manufacture and control during hydraulic pressure testing of the cooling path in hydraulic “cold” tests, and based on the results of such tests, it is necessary to reduce the operating pressure of the fuel in the cooling path and combustion products in the combustion chamber. This is one of the reasons for reducing the degree of expansion of combustion products in the nozzle and reducing efficiency. This requires new soldering processes, such as, for example, without installed collectors (the so-called collectorless soldering (RF patent 2465483 dated March 31, 2011)) with subsequent welding of the collectors and temperature control of the welded soldered parts to ensure the integrity of the solder of the solder joint, which somewhat complicates the technological process. process. The thermal state of the wall is exacerbated by the presence of an annular non-finned baffle under the collectors between the cooling paths of the minimum section of the nozzle and the exit section of the nozzle. Due to the increased temperature of this baffle connection, associated with a lack of cooling at a greater thickness, it is necessary to increase the coolant flow rate, increasing the pressure loss in the cooling path in the area of the baffle, increasing the inlet pressure to the nozzle cooling path, which inevitably increases the mass of the nozzle due to the strengthening of connections in the nozzle cooling path, or to reduce the surface heat flux density by applying coatings from the gas side, thus somewhat complicating the manufacturing process. With this design, an uneven temperature field appears on the partition, since on the one hand it is affected by a cooler with a low temperature after the pump, and on the other hand, by a cooler with an increased temperature after the cooling path of the most heat-stressed section of the chamber, namely, the section of the minimum section of the nozzle and cylindrical parts of the combustion chamber. As a result of the emerging temperature gradient on the baffle, thermal deformations of the cooled shell and profile distortion are possible even at insignificant temperature gradients. In addition, during ground testing of a chamber with a high-altitude nozzle as part of a high-altitude engine, the thermal effect of combustion products at the place of separation of combustion products, which coincides with the location of the baffle, further worsens the thermal state of the nozzle.

The objective of the proposed invention is to eliminate the above disadvantages, reduce the hydraulic resistance of the cooling path by reducing the temperature of the nozzle in the area of the transverse bridges and reduce the temperature unevenness of the nozzle wall and the combustion chamber, therefore, reducing the inlet pressure of the fuel at the inlet to the cooling path and reducing the mass of the nozzle and chamber.

The above objective of the invention is solved by the fact that in a known chamber of a liquid-propellant rocket engine containing a combustion chamber equipped with a cooling path with longitudinal channels with transverse jumpers, the input manifold for supplying the missing component in the gas generator has a minimum cross section towards the nozzle exit and the output manifold located at of the mixing head and a pipeline connected to the inlet manifold of the cooling path with longitudinal channels and transverse bridges of the nozzle, the outlet manifold of the cooling path of the latter is connected by a pipeline to the mixing head, in it sections of the transverse jumpers in the interface zone of the inlet manifolds of the nozzle and the combustion chamber are discontinuous and are placed alternately between the longitudinal channels in the circumferential direction, the inlet manifold of the nozzle is located between the minimum section of the nozzle and the inlet manifold of the combustion chamber cooling path, and the longitudinal channels of the combustion chamber cooling paths and nozzles and in the interface zone with the input manifolds, they are connected at the transverse jumpers alternately by radial channels with the input manifolds of the same name.

The above objective of the invention is also solved by the fact that in the well-known chamber of a liquid-propellant rocket engine, the walls of intermittent transverse jumpers in the input manifold interface zone in the radial direction are made of a V-shaped profile and oriented with their vertices in the opposite directions from the radial channels.

The proposed chamber of the liquid rocket engine is shown in the drawing (Fig. 1-4, Fig. 1 is a structural diagram of the operation of the chamber of the liquid rocket engine with the image of the direction of movement of the cooler, the image of the connections of the sections of the cooling path of the combustion chamber and the nozzle, including its sections: the section of the minimum Fig. 2 - top view and longitudinal section of the chamber; Fig. 3 - cross-section of the chamber in the plane of the coolant supply manifold to the cooling path of the nozzle outlet section and a longitudinal section along the axes of the channels in the manifold; Fig. 4 - cross-section of the chamber in the plane of the coolant supply manifold to the combustion chamber cooling path and a longitudinal section along the axes of the channels in the manifold Fig. 5 is a side view of the fins of the shell of the nozzle 34 of the cooling path 2 in the area of the collectors 5 and 12 of the coolant supply with the housing 36 removed), where the following units are shown:

1. Combustion chamber;

2. Cooling path;

3. Longitudinal channel;

4. Cross jumper;

5. Inlet manifold of the combustion chamber;

6. The minimum section of the nozzle;

7. Nozzle cut;

8. Nozzle;

9. Combustion chamber outlet manifold;

10. Mixing head;

11. Pipeline;

12. Nozzle inlet manifold;

13. Longitudinal channel of the nozzle;

14. Nozzle outlet manifold;

15. Pipeline;

16. Section of transverse jumpers;

17. The zone of interface of the inlet manifolds of the combustion chamber and the nozzle;

18. Intermittent section of the transverse bridge;

19. Longitudinal channel of the combustion chamber cooling path;

20. Longitudinal channel of the nozzle cooling path;

21. Radial channel of the inlet manifold of the nozzle;

22. Radial channel of the inlet manifold of the combustion chamber;

23. Plot of the minimum section of the nozzle;

24. V-shaped profile of the transverse partition;

25. The top of the V-shaped profile of the transverse partition;

26. Section of the mating longitudinal channel of the combustion chamber cooling path;

27. Section of the mating longitudinal channel of the nozzle cooling path;

28, 29. Longitudinal radial rib;

30 Wall of a transverse intermittent bulkhead of a V-shaped profile;

31. The wall of the transverse intermittent bridge of the V-shaped profile;

32. Outlet section of the nozzle;

33. Docking part of the nozzle shell;

34. Nozzle shell;

35. Overlay;

36. The body of the outlet section of the nozzle;

37. Under-collector wall of the nozzle cooling path;

38. Under-collector wall of the combustion chamber cooling path;

39. Housing of the second component.

The liquid-propellant rocket engine chamber contains a combustion chamber 1 equipped with a cooling path 2 with longitudinal channels 3 with transverse jumpers 4 for supplying the first component with an inlet manifold 5 behind a minimum section 6 towards the cut 7 of the nozzle 8 and an outlet manifold 9 located at the mixing head 10 and connected by pipeline 11 to the inlet manifold 12 of the cooling path 2 nozzles 8 with longitudinal channels 13 and transverse jumpers 4 of the nozzle 8. The outlet manifold 14 of the cooling path 2 nozzles 8 is connected by a pipeline 15 to the mixing head 10 of the combustion chamber 1. Sections 16 of the transverse jumpers 4 in the interface zone 17 of the inlet manifold 12 of the cooling path 2 of the nozzle 8 and the inlet manifold 5 of the combustion chamber 1 are discontinuous 18 and placed alternately between the longitudinal channels 13 in the circumferential direction. The inlet manifold 12 of the cooling path 2 of the nozzle 8 is placed between the minimum section 6 of the nozzle 8 and the inlet manifold 5 of the cooling path 2 of the combustion chamber 1, and the longitudinal channels 19 of the cooling path 2 of the combustion chamber 1 and the longitudinal channels 20 of the cooling path of the nozzle 8 in the interface zone 17 with the inlet collector 12 and inlet manifold 5 are connected at the transverse jumpers 4 alternately by radial channels 21 with the same inlet manifold 12 of the nozzle 8, and by radial channels 22 with the inlet manifold 5 of the combustion chamber 1. It should be said that the replacement of the assembly of two inlet manifolds 5 and 12 located under one housing on separate manifolds 5 and 12 spaced along the longitudinal axis of the chamber, regardless of the location relative to the section of the minimum section 19 of the nozzle 8, already reduces the rigidity of the section of the chamber housing and improves the reliability of the brazed shell in the area of the inlet manifolds 5 and 12. However, it is the location of the inlet manifold 12 nozzles closer to section 23 of the minimum c The cross-section 6 of the nozzle 8 provides a set of improvements in the design of the chamber both to reduce temperature gradients in the areas 16 of intermittent jumpers 4, and to improve soldering due to a decrease in the rigidity of the chamber body during soldering. Sections 16 of discontinuous transverse bridges 4 in the interface zone 17 of the inlet manifold 12 of the combustion chamber 1 of the inlet manifold in the radial direction are made of a V-shaped profile 24 and are oriented with their tops 25 in the opposite directions from the radial channels 22 and 23. Each mating longitudinal channel 19 of the cooling path of the combustion chamber 1 in section 26 and each mating channel 20 of the cooling path of the nozzle 8 in section 27 has a common longitudinal radial rib 28 on one side and a common longitudinal radial rib 29 on the other side. The common longitudinal rib 28 mates with the wall 30 of the transverse intermittent web 4 of the V-shaped profile 24, and the common longitudinal rib 29 mates with the wall 31 of the transverse intermittent web 4 of the V-shaped profile 24. The longitudinal rib 28, as well as the V-shaped profile 24 with one side is in contact with the fuel at the inlet to the inlet manifold 5 of the combustion chamber 1, and on the other side it is in contact with the fuel at the outlet of the cooling path of the combustion chamber (at the inlet to the inlet manifold 12 of the nozzle 8). The longitudinal rib 29, as well as the V-shaped profile 24, on the one hand, is in contact with the fuel at the inlet of the inlet manifold 5 of the combustion chamber 1, and on the other hand, it is in contact with the fuel at the outlet of the cooling path of the combustion chamber (at the inlet to the inlet manifold of the nozzle 12). One group of transverse jumpers 4 V-shaped profile 24 associated with the radial channels 22 of the inlet manifold 5 of the combustion chamber 1 is oriented to the cut 7 of the nozzle 8, and the second group of transverse jumpers 4 V-shaped profile 24 associated with the radial channels 21 of the inlet manifold 12 of the nozzle 8 is oriented to section 23 of the minimum section 6 of nozzle 8. The outlet section 32 of nozzle 8, starting from the section of the V-shaped profile 24 of the combustion chamber 1, is connected by welding along the mating part 33 of the shell 34 of the nozzle 8 (under the inlet manifold 5 of the combustion chamber 1), and with the help of the lining 35 with the body 36 of the outlet part of the nozzle. When using additive technologies in the manufacture of the collector assembly of the chamber and the subcollector wall 37 of the cooling path 2 nozzles, the subcollector wall of the cooling path 3 8 2 of the combustion chamber 1 with a V-shaped profile 24 transverse discontinuous jumpers 4, there is no need for soldering operations on the proposed chamber of a liquid rocket engine , in welding and milling operations for the manufacture of channels of the cooling path 2. The supply of generator gas to the combustion chamber 1 is provided using the housing 39 of the second component, which is part of the mixing head 10.

The camera liquid rocket engine in steady state operates as follows. The oxidizing generator gas (the second component) enters the combustion chamber 1 through the body of the second component 39 into the mixing head 10. The fuel (the first component) enters the inlet manifold 5 of the combustion chamber 1, cooling the walls of the cooling path 2 of the combustion chamber 1, enters the outlet manifold 9, and with the help of pipeline 11 enters the inlet manifold 12 of the nozzle 8. After cooling the nozzle 8, the fuel enters through the outlet manifold 14 of the nozzle 8 and the pipeline 15 into the mixing head 10 of the combustion chamber 1. As it moves from the inlet manifold of the combustion chamber 5 in radial channels 22 and further, the fuel enters only the longitudinal channels 19 of the cooling path 2 of the combustion chamber 1, which is facilitated by transverse intermittent sections 18 of the transverse bridges 4 made in the subcollector wall 38 of the cooling path 2 of the combustion chamber 1, cooling the subcollector wall 38 of the cooling path 2 of the combustion chamber 1 and (on one side) longitudinal radial ribs 28, then mixed with that with the same fuel flows in adjacent longitudinal channels and through longitudinal channels 19 enters the outlet manifold 9 of the combustion chamber 1. The location of the internal parts of the V-shaped profiles 24 of the transverse partitions under the extreme radial channels 22 and in close proximity to the radial channels 22 of the inlet manifold 5 of the combustion chamber 1 provides a minimum portion of the stagnant fuel zone, and the implementation of the V-shaped partition wall also contributes to the cooling of the outer part of its wall 30 by fuel entering through the longitudinal channels 20 in the cooling path 2 of the nozzle 8. Moreover, along one side of the longitudinal radial ribs 28, the fuel is cooled by the chamber combustion 1 moves in one direction, and along the other sides of the longitudinal radial ribs 28, the fuel cooling nozzle 8 moves in the other direction. Both fuel flows are subject to heating, but the average temperature of the longitudinal rib, as being washed by fuel with different temperatures, is close to the same throughout the sub-collector wall 37 of the cooling path 2 of the nozzle 8 and the sub-collector wall 38 of the cooling path 2 of the combustion chamber 1.

Similarly to the above diagram of the movement of fuel along the section of the subcollector wall 38 of the cooling path 2 of the combustion chamber 1, the fuel moves along the section of the subcollector wall 37 of the cooling path 2 of the nozzle 8. As it moves from the inlet manifold 12 of the nozzle 8, only into the longitudinal channels 20 of the cooling path 2 of the nozzle 8, which is facilitated by the transverse intermittent sections 18 of the transverse bridges 4 made in the subcollector wall 37 of the cooling path 2 of the nozzle 8, cooling the subcollector wall 37 of the cooling path 2 of the nozzle 8 and the longitudinal radial ribs 29 (on one side) , then mixes with the same fuel flows in adjacent longitudinal channels and enters the outlet manifold 14 of the nozzle 8 through the longitudinal channels 20. 12 nozzles 8 providing there is a minimum section of the stagnant fuel zone, and the implementation of the V-shaped partition wall also contributes to the cooling of the outer part of its wall 30 by the fuel coming through the longitudinal channels 19 of the cooling path 2 of the combustion chamber 1. Moreover, along one side of the longitudinal radial ribs 29 fuel cooling of the nozzle 8 moves in one direction, and along the other sides of the longitudinal radial ribs 29, the fuel cooling of the combustion chamber 1 moves in the other direction. Both fuel flows are subject to heating, but the average temperature of the longitudinal radial rib 29, as being washed by fuel with different temperatures, is close to the same throughout the sub-collector wall 37 of the cooling path 2 of the nozzle 8 and the sub-collector wall 3 8 of the cooling path 2 of the combustion chamber 1.

Due to this chamber design, a reduced and uniform temperature of the wall, longitudinal radial ribs 28 and 29 and transverse intermittent bridges 4 is achieved at a lower fuel flow rate in the longitudinal channels 19 of the cooling path 2 of the combustion chamber 1 and the longitudinal channels 20 of the cooling path 2 of the nozzle 8, which will allow reduce the hydraulic resistance of the fuel in the cooling path 2.

The application of the invention is to eliminate the above disadvantages, reduce the hydraulic resistance of the cooling path by reducing the temperature of the nozzle in the area of the transverse bridges, reducing the temperature unevenness of the wall of the nozzle and the combustion chamber.

Claims (2)

1. The chamber of a liquid rocket engine, containing a combustion chamber, equipped with a cooling path with longitudinal channels with transverse jumpers, an input manifold for supplying the component missing in the gas generator with a minimum cross section towards the nozzle exit, and an output manifold located at the mixing head and connected by a pipeline with the inlet manifold of the cooling path with longitudinal channels and transverse jumpers of the nozzle, the outlet manifold of the cooling path of the latter is connected by a pipeline to the mixing head, characterized in that in it sections of the transverse jumpers in the interface zone of the inlet manifolds of the nozzle and the combustion chamber are discontinuous and placed alternately between the longitudinal channels in in the circumferential direction, the inlet manifold of the nozzle is located between the minimum section of the nozzle and the inlet manifold of the combustion chamber cooling path, and the longitudinal channels of the combustion chamber and nozzle cooling paths in the interface zone with the inlet manifolds and are connected at the transverse jumpers alternately by radial channels with the same input manifolds. 2. The chamber of the liquid-propellant rocket engine according to claim 1, characterized in that the walls of the discontinuous transverse jumpers in the input manifold interface zone in the radial direction are made of a V-shaped profile and are oriented with their vertices in the opposite directions from the radial channels.

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