Engine injection device and wall surface temperature control method thereof
A temperature control method and engine technology, which is applied in the direction of rocket engine devices, machines/engines, jet propulsion devices, etc., can solve problems such as inaccurate measurement, achieve stable and convenient installation, avoid data abnormalities, and avoid insulation failure.
Inactive Publication Date: 2021-06-18
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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Problems solved by technology
[0006] The invention aims to solve the problem that the temperature sensor is generally installed on the outer cooling jacket in the wall surface temperature measurement of the current engine test ejection device, which cannot be measured accurately, and provides a temperature control method for the engine ejection device and its wall surface
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[0039] The technical solutions of the present invention will become apparent from the embodiments and the accompanying drawings of the present invention, as will be described below.
[0040] Such as Figure 4 with Figure 6 As shown, an engine leading device including inner layer introduction tube 1, an outer layer cooling jacket 2, which is arranged on the inner leading tube 1, and is disposed on the cooling jacket 2. Temperature test system 3;
[0041] The temperature test system 3 includes at least two temperature measurement units disposed on the inner layer lead tube 1, each of which is disposed on different temperature regions, respectively; three different temperature regions are at the inner layer. 1 of the inlet, middle and exit; the temperature unit includes a positive electrode heat coupling 31, a negative electrode thermal occlusion 32, a ceramic sleeve 33, a ceramic sleeve 33, an external thermal occasion 31, and a negative electrode thermal occasion 33, The embedded is...
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The invention relates to an engine test injection device wall surface temperature control technology, in particular to an engine injection device and a wall surface temperature control method thereof. The engine injection device and the wall surface temperature control method thereof aims to solve the problem that in current engine test injection device wall surface temperature measurement, a temperature sensor is generally installed on an outer layer cooling jacket, and accurate measurement cannot be achieved. According to the technical scheme, the engine injection device comprises an inner-layer injection pipe, the outer-layer cooling jacket arranged on the inner-layer injection pipe in a sleeving mode and a temperature testing system arranged on the cooling jacket; the temperature testing system comprises a temperature measuring unit; the temperature measuring unit comprises a positive thermocouple wire, a negative thermocouple wire, a ceramic sleeve sleeving the positive thermocouple wire and the negative thermocouple wire, and an embedded isolation pipe sleeving the ceramic sleeve; the temperature measuring ends of the positive thermocouple wire and the negative thermocouple wire adopt twisted-pair structures and are welded on the outer wall of the inner-layer injection pipe; and the invention further provides a temperature control method for the wall face of the engine injection device.
Description
Technical field [0001] The present invention relates to an engine test, a wall temperature control technique, which specifically relates to a temperature control method of an engine leading device and a wall surface thereof. Background technique [0002] Such as figure 1 with figure 2 As shown, in the high-altitude simulation assay of the liquid rocket engine, the engine is typically designed to use the introduction device to realize the simulation of the power of the thrust chamber nozzle, the concentrating device of the sandwich water-cooled structure is the core of the engine high-altitude simulation test. Equipment, its body structure includes inner layer introduction tube 01 and outer layer cooling jacket 02. [0003] In the engine ignition test, the high-temperature high pressure gas generated by the thrust chamber jet will directly generate high temperature convection and radiation effects in the inner wall surface of the introduction device inner introduction tube 01, in ...
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IPC IPC(8): F02K9/96
CPCF02K9/96
Inventor 乔江晖贺宏冷海峰丁佳伟白文义鱼凡超刘永伟潘思宇朱成亮耿直李谦朱小江翟文化赵涛
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST