A wide range simulated incoming flow heating device
A heating device with a wide range of technology, applied in jet engine testing, gas turbine engine testing, etc., can solve problems such as explosion hazards, and the range ratio of a single heating device cannot meet the test requirements, etc., to achieve small thermal inertia and improve work efficiency and preparation cycle, the effect of preventing the risk of cross-cavity
Active Publication Date: 2021-01-12
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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Problems solved by technology
[0006] The purpose of the present invention is to solve the technical problem that the existing combustion heating device has the risk of stringing chambers leading to explosion hazards, and the range ratio of a single heating device cannot meet the test requirements of the engine test for the whole airspace flight simulation, and provides a wide range Simulated incoming flow heating device
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[0034] The content of the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.
[0035]The present invention provides a wide range of simulated incoming flow heating devices. The head 8 of the heating device realizes integral processing, which fundamentally solves the risk of cross cavity, and the head 8 of the heating device is structurally connected with the body of the heating device. 9 Realize separate installation, solve the problem of test bench use, easy inspection and maintenance. At the same time, in order to meet the flight simulation requirements of the full airspace (envelope) of the ramjet, the overall full-scale performance test must be completed on a single heating device. The heating device in the form of pressure atomization in the past cannot meet the test requirements. After the igniter 6 works normally, three working fluids, liquid oxygen, alcohol, and air, are supplied to the he...
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The invention belongs to the field of direct connection tests of ramjet engines and provides a wide-range analog incoming flow heating device for solving the technical problem that an explosion hazardis caused by the risk of running to other cavities existing in the existing combustion heating device and the range-variable ratio of a single heating device cannot meet the test requirement of full-airspace flight simulation of the engine test. The device comprises a heating device head, a heating device body and a heating device throat; the heating device head comprises an injector, an igniter,an alcohol connecting pipe nozzle, a liquid oxygen connecting pipe nozzle, a first air connecting pipe nozzle, a second air connecting pipe nozzle, a third air connecting pipe nozzle, an alcohol airatomizing nozzle and a liquid oxygen air atomizing nozzle; the injector is of a disc structure and is sequentially provided with a first air cavity, an annular alcohol cavity, an annular liquid oxygencavity, a second annular air cavity and a third annular air cavity which are concentrically arranged and do not communicate with each other from the axis to the outside, and the injector is integrated with the alcohol air atomizing nozzle, the liquid oxygen air atomizing nozzle and an air nozzle.
Description
technical field [0001] The invention belongs to the field of direct connection test of ramjet, and in particular relates to a heating device for simulating incoming flow in a wide range. Background technique [0002] The ramjet engine used in the flight test draws air from the atmosphere as the working fluid. Its internal and external flow conditions are determined by the atmospheric parameters of a certain flight altitude: static pressure, static temperature and flight Mach number. Its independent parameters are the total pressure, total temperature and flight Mach number. In the direct connection test simulation technology, the independent relationship between total pressure, total temperature and flight Mach number is used to simulate the parameters of the airflow at the inlet of the engine inlet by heating the incoming air to achieve the total temperature to be simulated. [0003] The inflow heating is to heat the airflow at the inlet of the engine inlet. The specific t...
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IPC IPC(8): G01M15/14
Inventor 麻军德史超曹文庆王岳付永涛徐玲虞虔唐云龙侯昱舟龚文祥余爱英章萌郭宁敏
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST