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Rocket nozzle and control method for combustion of the exhaust gas flow in rocket engine

A rocket engine, combustion gas technology, applied in rocket engine installation, engine manufacturing, engine components and other directions, can solve problems such as strong vibration

Inactive Publication Date: 2009-09-23
MITSUBISHI HEAVY IND LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, since the flow of combustion gas tends to separate from the inner wall surface of the second-stage nozzle 116 at the upstream position from the nozzle outlet 113 when the height immediately after the transition is low, the vibration will be strong

Method used

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  • Rocket nozzle and control method for combustion of the exhaust gas flow in rocket engine
  • Rocket nozzle and control method for combustion of the exhaust gas flow in rocket engine
  • Rocket nozzle and control method for combustion of the exhaust gas flow in rocket engine

Examples

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Effect test

no. 1 example

[0032] Figure 7 A rocket motor 1 according to a first embodiment of the invention is shown. The rocket engine 1 includes a fuel cabin 2 , an oxidizer cabin 3 , a fuel turbo pump 4 , an oxidant turbo pump 5 and a rocket nozzle 8 . The fuel turbine pump 4 includes a pump 4a and a turbine 4b that rotates together with the pump 4a. The oxidizer turbo pump 5 includes a pump 5a and a turbine 5b rotating together with the pump 5a.

[0033] The rocket nozzle 8 includes an injector 6, a combustion chamber 7, a double bell nozzle 10, and a gas introduction portion 40A. The combustion chamber 7 is provided with a cooling path 7 a for cooling the wall surface of the combustion chamber 7 . The double bell nozzle 10 includes a first stage nozzle 20 as a portion from the throat 11 to an inflection point 12 and a second stage nozzle 30 as a portion from the inflection point 12 to a nozzle outlet 13 . The inflection point 12 is disposed between the first stage nozzle 20 and the second stag...

no. 2 example

[0044] The rocket engine 1 according to the second embodiment of the present invention is configured the same as the rocket engine 1 according to the first embodiment of the present invention except that the gas introduction portion 40A is replaced with the gas introduction portion 40B. refer to Figure 10 , in addition to the duct 41 , manifold 42 , introduction path 43 and inlet 45 described above, the gas introduction portion 40B includes an exhaust pipe 46 branched from the duct 41 and a valve 47 provided to the exhaust pipe 46 . The valve 47 is opened and closed according to the control signal 71 . When valve 47 is open, part of the turbine exhaust gas from oxidizer turbo pump 5 is introduced from inlet 45 into space 80 and the remaining part is expelled to atmosphere through exhaust pipe 46 . When valve 47 is closed, the entire turbine exhaust from oxidant turbopump 5 is directed from inlet 45 into space 80 .

[0045] The height H of the rocket containing the rocket mo...

no. 3 example

[0050] The rocket engine 1 according to the third embodiment of the present invention is configured the same as the rocket engine 1 according to the first embodiment of the present invention except that the gas introduction portion 40A is replaced with the gas introduction portion 40C. refer to Figure 11 , in addition to the pipe 41, manifold 42, introduction path 43, and inlet 45 described above, the gas introduction part 40C also includes a three-way valve 51 provided on the pipe 41 and a three-way valve provided at the side of the inflection point 12 of the manifold 42. Manifold 52 , whereby manifold 52 is adjacent to manifold 42 . The three-way valve 51 connects one of them to the oxidant turbopump 5 by switching between the manifold 42 and the manifold 52 according to the control signal 72 . The turbine exhaust gas from the oxidizer turbo pump 5 flows into the manifold 42 or the manifold 52 according to the switching state of the three-way valve 51 .

[0051] refer to ...

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PUM

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Abstract

A rocket nozzle (8) includes a dual-bell nozzle (10) and a gas introducing section (40A, 40B, 40C, 40D) configured to introduce gas into space (80) surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle (20) bell-shaped and surrounding an upstream portion (81) of the space, and a second stage nozzle (30) bell-shaped and surrounding a downstream portion (82) of the space. The dual-bell nozzle has an inflection point (12) between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet (45, 63) provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.

Description

technical field [0001] The present invention relates to a rocket nozzle and method for controlling the flow of combustion gases within a rocket engine. Background technique [0002] Figure 1 shows a bell nozzle 100A as a rocket nozzle. When the flow path cross-sectional area at the throat 101A is At and the flow path cross-sectional area at the nozzle outlet 102A is A1, the expansion ratio eA of the bell nozzle 100A is determined by the ratio between A1 and At (A1 / At) said. Figure 2 shows a bell nozzle 100B as a rocket nozzle. When the flow path cross-sectional area at the throat 101B is At and the flow path cross-sectional area at the nozzle outlet 102B is A2, the expansion ratio eB of the bell nozzle 100B is represented by the ratio of (A2 / At). Here, A2 is greater than A1, and thus eB is greater than eA. [0003] The specific impulse, which represents the performance of the rocket nozzle, is known. The specific impulse varies according to the expansion ratio and the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/97
CPCF02K9/972F02K1/38F05B2250/713F02K9/46F02K9/82F02K9/48F02K9/58F05D2250/713F02K9/97F02K9/56
Inventor 木村龙也川又善博丹生谦一
Owner MITSUBISHI HEAVY IND LTD
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