A set of large diameter rocket thrust chamber with discharging regenerative cooling partition plates

Active Publication Date: 2018-04-24
李达
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The gas introduced from the turbine exhaust inlet pipe is only oxygen-rich, which does not meet the status quo of hydrogen-oxygen engine turbines driven by hydrogen-rich gas

Method used

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  • A set of large diameter rocket thrust chamber with discharging regenerative cooling partition plates
  • A set of large diameter rocket thrust chamber with discharging regenerative cooling partition plates
  • A set of large diameter rocket thrust chamber with discharging regenerative cooling partition plates

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Embodiment Construction

[0039] Figure 1 to Figure 9 It is a preferred embodiment of the present invention for a group of large diameter rocket thrust chambers that use exhaust regeneratively to cool the diaphragm.

[0040] Such as figure 1 , figure 2 with image 3 As shown, a large-diameter basic type thrust chamber is composed of a head 1, a body 2 and a partition 3 and welded as a whole. The connecting parts of the head 1 and these three parts include a bearing seat 4, a flange 5, a porous inner cone shell 6, an outer cone shell 7, a turbine exhaust introduction pipe 8, a first bearing connector 9, a second bearing Force connector 9A, third load-bearing connector 9B, connection collection ring 10, injector plate 11, injection arc section plate group 12, injection radial plate 13, head-body connecting plate 14, ignition fuel collector 15 and ignition fuel enters tube 16. The head 1 is a reinforced double-cone shell big head 1A that adds a third load-bearing connector 9B to more firmly connect...

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PUM

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Abstract

The invention relates to a set of large diameter rocket thrust chamber with discharging regenerative cooling partition plates. There are ten kinds such as a liquid oxygen kerosene large or oversize orgiant thrust chamber, a hydrogen oxygen large or oversize thrust chamber, a hydrogen peroxide large or oversize or giant thrust chamber and a hydrogen-rich hydrogen oxygen large or oversize thrust chamber. The regenerative cooling partition plates with fine and long axial holes and with or without end heads in a 13(10) area, a 29(22) area and a 45(34) area are provided, and thus high frequency unstable combustion can be effectively inhibited. An inner cooling improving mode of annular gaps is further provided, so that a liquid film or a gas film is attached to the wall more evenly. A reinforced double-conical-shell head additionally provided with a third bearing connecting piece and a fourth bearing connecting piece is arranged. Axial holes used for gas nozzles and small diameter holes used for liquid nozzles form a straight-flow type injector. The thrust chamber is simple in structure and good in generality, and the number of parts is reduced greatly. The technical difficulty is low,the lead time can be shortened, and the cost is reduced. The hydrogen peroxide thrust chamber and the hydrogen oxygen thrust chamber can be reused for 25-200 times and 2-25 times correspondingly. Theset of large diameter rocket thrust chamber is suitable for manned lunar-landing Mars-landing rocket engines and the like.

Description

technical field [0001] The invention relates to a group of large-diameter rocket thrust chambers that use exhaust regeneration to cool partitions, and belongs to the technical field of liquid oxygen kerosene, hydrogen oxygen and hydrogen peroxide rocket engines. Background technique [0002] Although the super-large and large rocket thrust chambers proposed by me (201710449940.2, 201710449991.5 and PCT / CN2017 / 000482) have many advantages and are worthy of selection, there are also some shortcomings. Mainly use regenerative cooling partitions with liquid inlet and outlet pipes, and the structure is more complicated. There are advantages and disadvantages to using diaphragm coolant as cooling film liquid in thrust chamber. The advantage is to improve the cooling performance of the thrust chamber, etc. The disadvantage is that some form three-component propellant thrust chamber, increase the complexity of the engine supply system, and increase the storage tank and supply pipe...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/64F02K9/52
CPCF02K9/52F02K9/62F02K9/64
Inventor 葛明龙其他发明人请求不公开姓名
Owner 李达
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