The invention provides a high-temperature combustion-gas flow supersonic wind tunnel test system and relates to the technical field of aircraft thermal protection ground test The system comprises a heater, a supersonic nozzle, a test cabin, a diffuser and an exhaust system One end of the heater is connected with an external energy system; one end of the supersonic nozzle is fixedly connected with the heater, and the other end of the supersonic nozzle is fixedly connected with the test cabin; the diffuser is fixedly arranged at one end of the test cabin; and one end of the exhaust system is fixedly connected with the diffuser, and the other end of the exhaust system is connected with the outside world directly The high-temperature combustion-gas flow supersonic wind tunnel test system is a system having hundred-megawatt power and meter-scale jet size, and the power thereof reaches more than 200 megawatts, and the jet size reaches 15 m; and aircraft thermal protection system global and regional 1:1 large-size model heat check can be realized

High-temperature combustion-gas flow supersonic wind tunnel test system

The invention provides a hybrid pressure stabilizing chamber device. The device includes a gas inlet transfer section, a hybrid pressure stabilizing section and a pressure measurement transfer section; and a high-temperature airflow generated by a heater flows into the gas inlet transfer section of the hybrid pressure stabilizing chamber, a normal-temperature gas is injected in the gas inlet transfer section in a radial direction, the normal-temperature gas and the high-temperature airflow generated by the heater are subjected to mixing and flow stabilization in the hybrid pressure stabilizingsection, the high-temperature airflow of which airflow temperature is adjusted and airflow pulsation is reduced flows into the pressure measurement transfer section, and an airflow of which the airflow pressure is measured enters downstream test devices such as test spray tubes. The hybrid pressure stabilizing chamber device provided by the invention realizes the functions of gas entering and sealing connection in the gas inlet transfer section, and solves the thermal protection and thermal strain problems of partial leakage because the inlet portion of the hybrid pressure stabilizing chamberis susceptible to heat shrinkage.

Hybrid pressure stabilizing chamber device

A disclosed wind tunnel type turbine generator comprises a wind tunnel apparatus with thermal insulation property, the wind tunnel apparatus comprises an air-inflow constriction section, a test section and an exhaust expansion section; the front end of the air-inflow constriction section is provided with an air compressor; the front end of the air compressor is provided with a heating member; and the test section is inside provided with an airflow turbine connected with a power generator. Therefore, by heating air passing through the air compressor by means of the heating member, a high-speed airflow is formed in the test section of the wind tunnel apparatus and drives the airflow turbine to rotate to generate electric power, and also steam is prevented from being coagulated at an outlet of the airflow turbine because of low temperature, and thus the electric generating effect is guaranteed.

Wind tunnel type turbine generator

The invention provides a high-temperature continuous nitrogen heater. The high-temperature continuous nitrogen heater comprises a cylinder, a water cooling positive electrode, a water cooling negative electrode and a heating element; the heating element is mounted on the axis of the cylinder, and one end thereof is connected with the water cooling positive electrode through a slide transfer piece; the water cooling positive electrode is connected with a power supply by penetrating out of a water cooling end surface flange tightly connected to one end of the cylinder; the other end of the heating element penetrates out of a graphite baffle plate at the other end of the closed cylinder; upper and lower two water cooling negative electrodes mounted on the heating element through an electrode transfer disc are connected with the power supply after penetrating out of through holes in the wall of the cylinder; the heating element is a sandwich layer structure consisting of a graphite straight pipe on the outer layer and a graphite straight pipe with a spiral fin on the outer pipe wall on the inner layer; a spiral channel is formed between the outer-layer pipe and the inner-layer pipe through the spiral fin; and a through hole is formed in the slide transfer piece connected to one end of the heating element. The high-temperature continuous nitrogen heater solves the difficulties of thermal expansion of the heating element and high-current electric conduction, and can realize continuous heating of nitrogen currents.

High-temperature continuous nitrogen heater

The invention discloses a heterogeneous feature subsets ensemble (HFSE) algorithm-based test section Mach number modeling method, and belongs to the technical field of computer applications The method comprises the steps that 1: based on a subsonic velocity one-dimensional isentropic flow theory, a wind tunnel test section Mach number is determined by a stilling chamber total pressure and a plenum chamber static pressure, so that NARX total pressure and static pressure model structures are established firstly; 2: an HFSE algorithm is proposed for fitting a nonlinear function of an NARX model, and heterogeneous sub-models are built in one-dimensional feature subsets of an FSE by taking a Fixed-size LS-SVM and an ELM as heterogeneous based learning machines; and 3: predicted values of HFSE-NARX total pressure and static pressure models are substituted into an empirical formula to obtain an HFSE Mach number model The model can reduce the scale of a sub-model set, improve the Mach number prediction precision, and meet the requirement of a mean square root error smaller than or equal to 0015

Heterogeneous feature subsets ensemble algorithm-based test section Mach number modeling method

FIELD: physics.SUBSTANCE: disclosed is a method of generating a stream and a continuous-action wind tunnel which covers the entire hypersonic range of speeds with Mach number M?5, wherein to generate a high-pressure gas, liquefied gas is used instead of multiple-stage compressors. The method involves creating a vacuum in a vacuum chamber, generating a high-pressure gas and controlling pressure thereof; heating the gas, pumping the gas from the vacuum chamber is carried out using cryopumps; gas from the vacuum chamber is chilled on cryopanels into a solid phase; and the cryopanels are regenerated by releasing gas at a higher pressure and temperature into the insulated cavity of the cryopump. The liquefied gas obtained as a result of regeneration is fed into a reservoir for storing liquefied gas which, when necessary, is converted to a high-pressure gas and fed into the reservoir for storing high-pressure gas and used in systems for generating, controlling pressure and heating the gas. The apparatus has a high-pressure gas source with a pressure control system, a gas heater, a hypersonic nozzle, a working part, a diffuser, a system for cooling gas after passing through the working part, a vacuum chamber, pumps for preliminary and final pumping of gas from the vacuum chamber. The vacuum chamber is evacuated using cryopumps in which gas is not released from the evacuated chamber but is condensed into a solid phase on pre-cooled cryopanels. The cryopanels are made from porous metal with an open pore system. Pulsed operating mode of the cryopumps, i.e. pre-chilling of cryopanels before operation and in intervals between launches, and the porous cryopanels enable to "recycle" virtually any gas flow through the hypersonic nozzle. The outer surface of the hypersonic nozzle inside the working part of the wind tunnel is provided with coils for cooling the nozzle walls, wherein the system for cooling the high-pressure gas coming from the working part is placed inside the vacuum chamber. Furthermore, the wind tunnel has a liquefied gas reservoir with a transfer pump and expander-generator sets for generating electrical energy.EFFECT: faster gas pumping, low power consumption when producing high-pressure gas, longer operation of a wind tunnel, wider range of analysed models with invariable geometric parameters of the nozzle outlet section.2 cl, 1 dwg

Method of generating gas stream in hypersonic rarefied-air wind tunnel and wind tunnel

FIELD: physics. ^ SUBSTANCE: disclosed is a method of generating gas flow in the working section of a wind tunnel and a wind tunnel, in which a compressor rotates through a jet of liquefied gas and (or) cold high-pressure gas obtained from a condensate, flowing from jet nozzles installed on the rotor of the compressor, and (or) from hollow blades of the compressor, which enables to considerably lower temperature of the gas after the compressor compared to existing methods. Excess gas from the wind tunnel is first directed into pressure-reducing-generating unit, where electrical energy is generated and gas is cooled through its expansion in the turbine, and the gas is further cooled when it flows into a vacuum chamber and liquefied on cryopanels installed therein, which are first cooled (between launches into the wind tunnel) by a cooling machine to temperature lower than the condensation temperature of the gas used. The cryopanels are made from porous metal and have pore surface area per unit mass which is two or three orders higher than that of cryopanels made from solid metal. The liquefaction intensity is proportional to the surface area of the contact of the gas with the surface of the cooled cryopanel. Hence a small cooling apparatus can efficiently cool large portions of gas over a short period of time. The liquefied gas is collected in a reservoir and used to rotate the compressor. ^ EFFECT: reduced loss of energy when generating gas flow, increased uniformity of flow in the working section. ^ 5 cl, 4 dwg

Method of generating gas flow in working section of wind tunnel and wind tunnel

FIELD: mechanical engineering.SUBSTANCE: method includes producing high-pressure gas of liquid gas by means of its gasification, gas pressure regulation and heating, cooling nozzle walls, test section and diffuser, cooling working gas in gas cooler, creating negative pressure in vacuum chamber. Gas evacuation from vacuum chamber is performed using cryogenic condenser pumps (CCP) by freezing out working gas on cryopanels into solid phase. When limit thickness of condensate layer is exceeded the cryopanels are reconditioned by filling isolated CCP cavity with dried atmospheric air, liquefied gas obtained as a result of reconditioning is pumped out for storage in tank and gasified in order to maintain required pressure in high-pressure gas tank using energy of dried atmospheric air. To cool working gas in gas cooler liquefied gas is used, and obtained high-temperature and high-pressure gas is directed to high-pressure gas tank and/or used in gasificator. In device for vacuum chamber exhausting CCP are used where gas is not ejected from vacuum cavity, but condenses into solid phase on chilled down to T=10÷25 K cryopanels. To improve characteristics of existing CCP it is proposed to use pulse mode of their operation, and to make cryopanels of porous metal with open pore system.EFFECT: higher flow rate of evacuated gas, lower energy consumption during high-pressure gas generation, liquid gas gasification, working gas heating and cooling, longer time of ADT operation, decrease in its dimensions.4 cl, 1 dwg

Kekhvajants Valerij Grigor Evich

Papers

Method of generating gas stream in hypersonic rarefied-air wind tunnel and wind tunnel

Method of generating gas flow in working section of wind tunnel and wind tunnel

Method of gas flow creation in aerodynamic tunnel and aerodynamic tunnel