RU2579293C1 - Liquid propellant engine with thrust vector control - Google Patents

Abstract

FIELD: rocket science.

SUBSTANCE: invention relates to rocketry, particularly, to liquid-propellant engines with controlled thrust vector. Liquid propellant engine with controlled thrust vector comprises chamber to swing in journals in the main stabilization planes, main components on the periphery of the engine along its axis, turbo pump unit with main high-pressure pumps and booster units, outputs of the pumps which are made in the form of spiral bends with conical nozzles and are connected in the latter to inputs of the main pumps at the periphery of the chamber with two pairs of two mutually perpendicular series of flexible pipelines in the form of bellows parallel to the main planes of stabilization and connected by curvilinear branch pipes, according to the invention in charge centrifugal pumps are installed by its inputs coaxial lines of supply components, and conical nozzles outlets along longitudinal axes of symmetry of the first towards high-pressure pumps and the nearest bellows flexible pipelines, the booster pump one component is made with possibility of rotation of rotor in opposite direction from the direction of rotor rotation booster another component.

EFFECT: invention provides reduced radial dimensions of liquid propellant engine seal engine layout and thereby reduced engine weight.

1 cl, 6 dwg

Description

The invention relates to the field of rocket science, in particular to liquid-propellant rocket engines with a controlled thrust vector, and can be used in liquid rocket engines running on liquefied natural gas and liquid oxygen, and more particularly, to a device for a single-chamber liquid rocket engine with a controlled thrust vector, designed for a propulsion system consisting of a bunch of several engines, for which it is important to ensure minimum overall dimensions, especially radial ones.

Known liquid rocket engines with a controlled thrust vector containing a chamber with the ability to swing in pins in the main stabilization planes, component supply lines on the periphery of the engine along its axis, a turbopump assembly with centrifugal pumps (see book edited by Osipov S.O.A.A. Alexandrov et al. “Launch vehicles.” M.: Military Publishing, 1981. p. 203 Fig. 6.1. And p. 232 Fig. 7.3a.)

On such engines, thrust vector control is provided by rocking the camera or the entire engine in the main stabilization planes by means of steering gears located in the rocket stabilization planes, that is, in vertical planes passing through the axles of the gimbal. The line for supplying one of the components to the engines in a bundle is placed along the longitudinal axis of the propulsion system in the central part of the tank of the other component, which complicates the layout of the propulsion system, since it is necessary to solve the problem of laying the pipeline of one of the components through the tank cavity of the second component using a tunnel pipeline.

Also known is a liquid-propellant rocket engine with a controlled thrust vector, comprising a chamber with the possibility of swinging in pins in the main stabilization planes, component supply lines on the periphery of the engine along its axis, a turbopump unit with centrifugal main pumps, booster pumps, the outputs of which are made in the form of spiral outlets with conical pipes and connected at the latter with the inputs of the main pumps along the periphery of the chamber by two pairs of two mutually perpendicular successive flexible pipelines in the form of bellows parallel to the main planes of stabilization and connected by curvilinear tubes (see. Rocket-space technology. Scientific and technical collection. Calculation, experimental studies and design of ballistic missiles with underwater launch. XV Makeevsky readings (October 25-26, 2009). Series XIV, Issue 1 (57) p. 104, Fig. 8 - prototype). In the specified engine, the location of the line for supplying one component from the outer part of the tank of another component without a tunnel pipe provides sufficient reliability of the system for supplying the component to booster pumps, greatly simplifies layout solutions for the placement of highways and tanks, and reduces the weight of the propulsion system. However, not at all locations of the booster pumps of the components supplied to their inputs from the line at the periphery of the engine, the minimum radial dimensions of the liquid-propellant rocket engine are provided. This is especially noticeable when arranging a bunch of engines with a controlled thrust vector, for which the presence of space in the compartment in the radial direction is especially important for ensuring the engine to swing. The need for free space not occupied by aggregates or highways becomes acute for propulsion systems, with the so-called “hot standby”, when a failed one of several ligament engines must be rejected by a significant angle to ensure that the remaining ligament engines swing. In addition, in the known liquid-propellant rocket engine with a controlled thrust vector, when the input line is run from the periphery of the tank to the pumps, additional hydraulic losses of the component are obtained at the forced curvature of the pipeline, which leads to a forced irrational pressure drop, which is already low due to pressure limitation in the tank , and increasing the likelihood of cavitation in booster pumps.

For liquid rocket engines using liquefied natural gas and liquid oxygen, the requirement of minimum radial dimensions also appears because of the need to provide space in the compartment for applying cryogenic thermal insulation to cryogenic highways. The need for minimum radial dimensions also arises during the modernization of launch vehicles during the forcing of liquid-propellant rocket engines by traction in the previous dimensions of the engine compartment.

The specified technical solution does not provide the minimum radial dimensions of the engine when using booster pumps with spiral outlets, which impose restrictions on the choice of the minimum compartment and on ensuring the use of the engine in cramped conditions of modernized launch vehicles when they are thrusted together in the same dimensions, which increases mass of the propulsion system, which is very important from the point of view of boosting efficiency.

The aim of the invention is to eliminate the above disadvantages and reduce the radial dimensions of a liquid rocket engine, seal the layout of the engine and thereby reduce the mass of the engine.

The above object of the invention is achieved by the fact that in a known liquid-propellant rocket engine with a controlled thrust vector containing a chamber with the possibility of swinging in pins in the main stabilization planes, a component supply line on the periphery of the engine along its axis, a turbopump assembly with centrifugal main high pressure pumps and booster pumps units, the pump outputs of which are made in the form of spiral bends with conical tubes and connected at the latter with the inputs of the main pumps on the periphery of the chamber two in pairs of two mutually perpendicular consecutive flexible pipelines in the form of bellows parallel to the main planes of stabilization and connected by curved nozzles, according to the invention, the pumping centrifugal pumps are installed with their inputs coaxially to the component supply lines, and the conical nozzles of the outputs along the longitudinal axis of symmetry of the first towards the high pressure pumps and the closest bellows flexible pipelines, and the booster pump of one component is made with the possibility rotor rotation in the opposite direction from the direction of rotation of the rotor of the booster pump of another component.

The invention is presented in Fig. 1-6, where:

1. Camera

2. Axle

3. Axle

4. The main plane of stabilization

5. The main plane of stabilization

6. Fuel supply line

7. The longitudinal axis of the engine

8. The oxidizer supply line

9. Turbopump assembly

10. Centrifugal main fuel pump

11. Centrifugal main oxidizer pump

12. Fuel Booster Pump

13. The booster pump of the oxidizer

14. The output of the fuel booster pump

15. Spiral tap of the fuel booster pump

16. The output of the spiral tap of the fuel booster pump

17. Conical branch pipe of the fuel feed pump

18. Inlet of the centrifugal main fuel pump

19. Flexible piping (closest to the fuel booster pump)

20. Flexible pipe (closest to the centrifugal main fuel pump)

21. Bellows (flexible pipe closest to the fuel booster pump)

22. Bellows (flexible tubing closest to the centrifugal main fuel pump)

23. Curved pipe

24. The longitudinal axis of the bellows (closest to the fuel booster pump)

25. The longitudinal axis of the bellows (closest to the centrifugal main fuel pump)

26. Fuel booster pump inlet

27. The output of the oxidizing booster pump

28. Spiral tap of the oxidizer booster pump

29. The output of the spiral outlet of the oxidizer feed pump

30. The conical pipe of the booster pump of the oxidizer

31. The input of the centrifugal main oxidizer pump

32. Flexible conduit (closest to oxidizer booster pump)

33. Flexible tubing (closest to the centrifugal oxidizer main pump)

34. Bellows (flexible conduit closest to the oxidizer booster pump)

35. Bellows (flexible conduit closest to the centrifugal oxidizer main pump)

36. Curved pipe

37. The longitudinal axis of the bellows (closest to the oxidizer booster pump)

38. The longitudinal axis of the bellows (closest to the centrifugal oxidizer main pump)

39. The input of the oxidizer boost pump

40. Gas turbine

41. Gas generator

42. Mixing head of the gas generator

43. Pipeline

44. Valve

45. The output of the centrifugal main oxidizer pump

46. Pipeline

47. Valve

48. Regulator;

49. The output of the centrifugal main fuel pump

50. The manifold of the combustible chamber

51. Pipeline

52. valve

53. The trigger valve oxidizer

54. Fuel start valve

55. Steering machine

56. Steering machine

57. Cardan

58. Traverse

59. Traverse

60. Frame

A liquid-propellant rocket engine with a controlled thrust vector comprises a chamber 1 with a possibility of swinging in pins 2 and 3 in the main stabilization planes 4 and 5, a fuel supply line 6 at the periphery of the engine along its longitudinal axis 7, an oxidizer supply line 8 at the periphery of the engine along its longitudinal axis 7, a turbopump unit 9 with a centrifugal main fuel pump 10 and a main oxidizer pump 11, a fuel booster pump 12, an oxidizer booster pump 13. The turbopump unit 9 is located in a plane located in along the longitudinal axis 7 of the chamber 1. The output 14 of the fuel feed pump 12 is made in the form of a spiral outlet 15 directed counterclockwise in a view from the side of the fuel supply line 6, which corresponds to the design of the fuel feed pump with the possibility of rotation counterclockwise. A conical pipe 17 is connected to the output 16 of the spiral outlet 15. Between the inlet 18 of the centrifugal main fuel pump 10 and the conical pipe 17 of the fuel feed pump 12, a pair of two mutually perpendicular consecutive flexible pipes 19 and 20 are mounted in the form of bellows 21 and 22 connected curved pipe 23. The bellows 21 is mounted with its longitudinal axis 24 parallel to the main plane of stabilization 4. The bellows 21 is the closest towards the conical pipe 17 of the booster pump fuel 12 and is located at a minimum distance from the chamber and from one of the trunnions 2 on the opposite side to the turbo pump unit 9 with respect to the chamber 1. The bellows 22 is mounted with its longitudinal axis 25 parallel to the main stabilization plane 5 and is located at a minimum distance from one from the pins 3. The inlet 26 of the fuel feed pump 12 is installed coaxially with the fuel supply line 6 and, therefore, along the longitudinal axis of the engine 7. The output 27 of the oxidizer pump 13 is made in the form of a spiral outlet 28 clockwise on de from the side of the oxidizer supply line 8, which corresponds to the execution of the oxidizer feed pump with the possibility of clockwise rotation and a direction of rotation opposite to the direction of rotation of the fuel shaking pump 12. A conical pipe 30 is connected to the outlet 29 of the spiral outlet 28. Between the inlet 31 of the centrifugal main pump oxidizer 11 and conical pipe 30 of the oxidizer booster pump 13 at the periphery of chamber 1, a pair of two mutually perpendicular successive flexible pipes 32 is mounted and 33 in the form of bellows 34 and 35 connected by a curved pipe 36.

The bellows 34 is mounted with its longitudinal axis 37 parallel to the main stabilization plane 4, but next in distance from the chamber 1 and the trunnions 3 in comparison with the location of the bellows 21 and on the reverse side with respect to the chamber 1 than the turbopump unit 9. The bellows 34 is closest to the conical pipe 30 of the oxidizer feed pump 13. The bellows 35 is mounted with its longitudinal axis 38 parallel to the main stabilization plane 5, is located on the other side of the chamber 1 than the bellows 21, and is centrifugally closest to the inlet 31 about the main oxidizer pump 11. The inlet 39 of the oxidizer feed pump 13 is installed coaxially with the oxidizer supply line 8 and, therefore, along the longitudinal axis of the engine 7. The turbopump 9 contains a gas turbine 40 connected to a gas generator 41, the mixing head 42 of which is connected by a pipe 43 to the installed on it with a valve 44 with an outlet 45 of the oxidizer pump 11, and a pipeline with a valve 46 installed thereon and a regulator 47 with an outlet 48 of the fuel pump 10. The chamber 1 contains a fuel manifold 49, which is connected to a wiring harness 50 with a valve 51 installed on it with the outlet 52 of the centrifugal main fuel pump 10. The start valve of the oxidizer 53 can be installed at the outlet of the booster pump of the oxidizer 13 or at the inlet to the booster pump of the oxidizer 13. The start valve of fuel 54 can be installed at the outlet of fuel booster pump 12 or at the entrance to the fuel booster pump 12. To control the thrust vector in the liquid rocket engine, steering machines 55 and 56 are installed. Camera 1 is installed in cardan 57 through trunnions 2 and 3. Cardan 5 7 is installed in traverses 58, 59. Traverses 58 and 59 are installed in frame 60.

A liquid-propellant rocket engine with a controlled thrust vector operates as follows. In the stationary mode of a liquid-propellant rocket engine with a controlled thrust vector, fuel is supplied from the fuel supply line 6 to the input 26 of the fuel pump 12, then to the output 14 of the fuel pump 12 through the spiral pipe 15 to the exit 16 of the spiral pipe and then through the conical pipe 17 to the flexible conduit 19. Into the flexible conduit 19, namely, into its bellows 21, the fuel enters from the conical pipe 17 with minimal hydraulic pressure loss than if the fuel enters through a curved pipe and they went. The fuel start valve 55, installed at the outlet 14 from the fuel feed pump 12, provides preliminary “cooling” of the fuel feed pump 12, and in the open position, the start valve 55 provides fuel to the fuel feed pump 12 and then through the flexible conduit 19, a curved pipe 23 through flexible conduit 20 to the centrifugal main fuel pump 10. To turn the fuel flow from the fuel line 6 to the bellows 21, a turn is used in the fuel priming pump 12 turning clockwise (in the view from the side of the fuel supply line 6), which is achieved by the coaxial arrangement of the conical pipe 17 of the fuel feed pump 12 relative to the bellows 21 and the coaxial arrangement of the fuel supply pipe 6 and the input 26 of the fuel pump. Thus, the radial dimensions of a liquid-propellant rocket engine are reduced by the value of the radius of rotation of the curved line that would have to be fulfilled. The fuel flows sequentially from the bellows 21 to the curved pipe 23, to the bellows 22 and to the inlet 18 of the centrifugal main fuel pump 10. In the centrifugal main fuel pump 10, the pressure rises and the fuel is supplied from the outlet 49 of the centrifugal main fuel pump 10 using the pipeline 46 through the regulator 48 into the mixing head 42 of the gas generator 41, and using the pipe 51 through the valve 52 it is supplied to the fuel manifold 50 of the chamber 1. The oxidizer comes from the oxidizer supply line 8 to the inlet 26 of the booster pump, oxidize For 13, then to the exit 27 of the oxidizer booster pump 13 through the spiral outlet 28 to the exit 29 of the spiral outlet of the oxidizer booster pump 28 and then through the conical pipe 30 to the flexible pipe 32. The oxidizer start valve 53 installed at the outlet 27 of the oxidizer booster pump 13, provides a preliminary “cooling” of the oxidizer booster pump 13, and its opening ensures that the oxidizer enters the centrifugal main oxidizer pump 11. In the flexible conduit 32, namely in its bellows 34, the oxidizer pops comes from a conical pipe 30 with less hydraulic pressure loss than if the oxidizing agent got on a curved line. To rotate the oxidizer flow from the oxidizer supply line 8 to the bellows 34, a clockwise rotation (as viewed from the side of the oxidizer supply line 8) is used in the oxidizer priming pump 13, which is achieved by performing a rotor (not shown) of the oxidizer priming pump with the possibility of clockwise rotation the arrow and the coaxial arrangement of the conical pipe 30 of the oxidizer booster pump 13 and relative to the bellows 34 and the coaxial arrangement of the oxidizer supply line 8 and the inlet 39 of the oxidizer booster pump litel 13.

Thus, by the value of the radius of rotation of the curved oxidizer line, which would have to be performed, the radial dimensions of the liquid propellant rocket are reduced. In addition, the execution of the oxidizer feed pump 13 with the possibility of rotating its rotor (not shown) clockwise eliminates the additional line between the conical pipe 30 and the bellows 34 and, therefore, hydraulic pressure loss, which makes it possible to bring the oxidizer feed pump closer to the longitudinal axis 7 of the liquid rocket engine, reducing radial dimensions. The oxidizing agent flows sequentially further from the bellows 34 to the curved pipe 36, to the bellows 35 and to the inlet 31 of the centrifugal main oxidizer pump 11. In the centrifugal main pump of the oxidizer 11, the pressure rises and the oxidizer is supplied from the outlet 45 of the centrifugal main oxidizer pump 11 via the pipe 43 through valve 44 into the mixing head 42 of the gas generator 41. The combustion products from the gas generator 41 enter the gas turbine 40, then into the chamber 1. Using the steering machines 55 and 56, the rocket rocket vigatelya stabilization in the main plane 4 and the principal plane of stabilization in 5 small radial dimensions, providing an arrangement of several liquid-propellant rocket engines, for example four, consisting of bundles (Fig. 6).

The specified technical solution can be used with other circuit solutions for powering the gas generator 41, gas turbine 40 of the turbopump unit 9 and chamber 1, which can be used in a liquid rocket engine using liquefied natural gas and liquid oxygen, with the fuel pump 12 and oxidizer 13 being in the same position relative to the inlet lines of the fuel 6 and the oxidizing agent 8, as well as the bellows 21 and 34 of the flexible pipelines 19 and 32 of the lines in accordance with the foregoing.

Preliminary studies of the proposed technical solution for the newly developed liquid-propellant rocket engine using liquefied natural gas and liquid oxygen showed the effectiveness of the proposed technical solution for the required reduction in radial dimensions and mass of the engine.

Claims (1)

A liquid-propellant rocket engine with a controlled thrust vector, comprising a chamber with the ability to swing in pins in the main stabilization planes, component supply lines on the periphery of the engine along its axis, a turbopump unit with centrifugal main high-pressure pumps and booster units, the pump outlets of which are made in the form of spiral outlets with conical nozzles and connected at the latter with the inputs of the main pumps on the periphery of the chamber by two pairs of two mutually perpendicular successive flexible pipelines in the form of bellows parallel to the main planes of stabilization and connected by curvilinear nozzles, characterized in that the booster centrifugal pumps are installed with their inputs coaxially to the component supply lines, and the conical outlet pipes along the longitudinal axis of symmetry of the first towards the high pressure pumps and the nearest flexible bellows, moreover, the booster pump of one component is made with the possibility of rotation of the rotor in the opposite direction from the direction of BP Rotating the booster pump rotor of another component.

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