CN104764610A - System for testing influence of testing gas contamination on performance of supersonic speed combustion chamber - Google Patents

Abstract

The invention discloses a system for testing the influence of testing gas contamination on the performance of a supersonic speed combustion chamber. High-enthalpy pure air which is conveyed and supplied by a resistive heater, water vapor which is sprayed in by a water adding system, carbon dioxide which is sprayed in by a carbon dioxide adding system and oxygen which is sprayed in by an oxygen adding system are added in a mixer to be fully mixed; all the gas enters a combustion chamber testing model through a spray pipe, a comparative test of the pure air and contamination gas can be made, and the influences of test working medium component composition difference and incoming flow parameter difference on the working process and performance of the supersonic speed combustion chamber can be effectively 'separated'. In the same test sequence, the pure air can be tested first, and then the contamination gas is correspondingly tested. The testing system saves the testing cost while improving the testing efficiency, and the working performance of a contamination gas adding system can well meet the requirement of simulating the parameters of the contamination gas at an inlet of the combustion chamber in the Ma4 flying state.

Description

A kind of test gas pollutes the pilot system to supersonic combustor performance impact

Technical field

The present invention relates to aero-engine test technology field, specifically, relate to the pilot system of a kind of test gas pollution to supersonic combustor performance impact.

Background technology

In supersonic combustor technical research process, ground experiment has key and basic effect.Ground experiment requires the high enthalpy gas state needed for Reality simulation flight environment of vehicle, and the extrapolation of supersonic combustor ground test data is applied to the uncertainty of Live Flying condition mainly from two aspects, i.e. the difference of inlet flow conditions and the difference of test model.The former except with flow field quality problem mutually outside the Pass, the mainly difference of incoming flow parameter and test constituent of air, namely relates to test air " polluting effect " problem; The difference of the latter mainly test model yardstick, structure and flight test model, namely relates to test model " scale effect " and structure influence problem.Test with Conventional pneumatic power, compared with Aerodynamic Heating structural test, in supersonic combustor performance test, " polluting effect " problem is more outstanding, due to its importance and complicacy, receive the extensive concern of scientific research personnel always and continue research.

In existing disclosed technical literature, as Japanese RJTF equipment " Comparison of Scramjet EnginePerformance in Mach 6Vitiated and Storage-Heated Air [J] .Journal ofPropulsion and Power; Vol.13 (5); September-October, 1997. "; The contrast test " Test Gas Vitiation Effects in a Dual-ModeScramjet Combustor [J] .Journal of Propulsion and Power; Vol.23 (3); July-August 2007. " that Virginia, The United States university carries out all can be considered strict contrast test, namely pure air is adopted, heat accumulating type heating or resistance heated, under the prerequisite of coupling important parameter, carry out contrast test with contaminated air incoming flow, can effectively isolate clean " polluting effect " in test air.

Eighties of last century nineties, Japan aerospace institute researchist has carried out the complete machine free jet contrast test of hydrogen fuel scramjet engine under simulated Mach number 6.0 state on punching engine testing equipment, " Comparison of Scramjet Engine Performance in Mach 6Vitiated andStorage-Heated Air [J] .Journal of Propulsion and Power; Vol.13 (5); September-October, 1997. ".RJTF equipment can select any one in accumulation of heat heating and combustion heating when simulated Mach number 6.0 state.This pollution contrast test system needs to possess burning heating equipment and pure air firing equipment simultaneously, makes the cost of test higher.Virginia university research personnel utilize resistance heating device, have carried out pure air incoming flow and H for hydrogen fuel supersonic speed combustion chamber ₂o/CO ₂contaminated air flows down direct-connected comparative experimental research, " Test Gas Vitiation Effects in a Dual-ModeScramjet Combustor [J] .Journal of Propulsion and Power; Vol.23 (3), July-August 2007. ".Utilize its existing electric resistance heater can produce the high enthalpy pure air incoming flow of the highest about 1300K, simultaneously by adding H in electric resistance heater inlet air incoming flow ₂o, CO ₂pollution components also fills into O ₂carry out simulated combustion heating contaminated air; Therefore possess on same equipment, model, to carry out direct-connected firing chamber contrast test ability under simulated flight Mach number 5.0 state.In test for contamination gas, oxygen mole fraction is 21%, and mates the firing chamber import stagnation temperature of two kinds of incoming flows.Refer to the dusty gas that University of Virginia uses in pertinent literature and add measure, but and unexposed relevant technical information, and in the dusty gas interpolation measure that uses of University of Virginia, O in pollution components ₂and CO ₂be joined before primary air heating, well heater oxidation, aging quickening can be caused, reduce the serviceable life of well heater, increase experimentation cost.

Summary of the invention

In order to avoid the deficiency that prior art exists, the present invention proposes the pilot system of a kind of test gas pollution to supersonic combustor performance impact; On the basis of pure air pilot system, by adding water vapor and carbon dioxide pollution component in mixer, pilot system being had and carries out simulated flight Mach number 4.0 state lower combustion chamber pollution contrast test ability on the same device.

The technical solution adopted for the present invention to solve the technical problems is: comprise pure air pilot system, dusty gas add-on system, fuel system, mixer, jet pipe, combustor test model, pure air pilot system comprises air source of the gas, main road air flow rate adjustment valve, electric resistance heater, air source of the gas is connected with electric resistance heater by main road air flow rate adjustment valve, mixer is between electric resistance heater and jet pipe, and jet pipe is connected with combustor test model; Dusty gas add-on system comprises water add-on system, carbon dioxide add-on system, oxygen add-on system, water piston cylinder in water add-on system is connected with water heater, carbon dioxide air source in carbon dioxide add-on system is connected with flow control valve and annex, water add-on system is connected by pipeline and mixer with carbon dioxide add-on system, and the oxygen source in oxygen add-on system is connected with mixer by flow control valve and annex; Tanks in fuel system is connected with combustor test model by flow control valve; Test procedure is as follows:

(1) regulate main road air flow rate adjustment valve and electric resistance heater power, by air heat to 800 ~ 1000K, after the flow field in combustor test model is stable, opens fuel feed system, carry out the supersonic combustor performance test of pure air incoming flow;

(2) after completing pure air test, regulate main road air flow rate adjustment valve and electric resistance heater power, after electric resistance heater outlet air reaches required state, open dusty gas add-on system, high temperature air, carbon dioxide, water vapor, oxygen mix by a certain percentage in mixer, and the oxygen mole fraction of mixer outlet gas is 21%; Wherein, in water heater, aqueous water is heated to the water vapor of 400 ~ 750 DEG C, sprays into mixer; After flow field in combustor test model is stable, open fuel system, spray to combustor test model by predetermined sequential control, burn, carry out the supersonic combustor performance test of dusty gas incoming flow;

(3) according to the supersonic combustor test figure collected, analysis pollution components water and carbon dioxide are on the impact of supersonic combustor performance.

Beneficial effect

A kind of test gas that the present invention proposes pollutes the pilot system to supersonic combustor performance impact, the carbon dioxide that the water vapor sprayed into water add-on system by the high enthalpy pure air added in a mixer via the defeated confession of electric resistance heater, carbon dioxide add-on system are sprayed into and the oxygen that oxygen add-on system sprays into fully mix, and enter into combustor test model by jet pipe; Fuel system sprays to combustor test model by predetermined sequential control, burning, realize the contrast test of pure air and dusty gas, effectively " separation " can go out test working medium component composition difference, incoming flow parameter difference to the impact of the supersonic combustor course of work and performance.In same test train number, first can carry out pure air test, then carry out corresponding dusty gas test, both improve test efficiency, and also saved experimentation cost simultaneously.The serviceability of dusty gas add-on system well can meet the firing chamber import contaminated air parameter under simulation Ma4 state of flight.

Accompanying drawing explanation

Below in conjunction with drawings and embodiments, a kind of test gas pollution of the present invention is described in further detail the pilot system of supersonic combustor performance impact.

Fig. 1 is the pilot system schematic diagram that test gas pollutes to supersonic combustor performance impact.

In figure:

1. air source of the gas 2. main road air flow rate adjustment valve 3. electric resistance heater 4. mixer 5. jet pipe 6. combustor test model 7. oxygen source 8. tanks 9. water heater 10. water piston cylinder 11. carbon dioxide air source 12. oxygen add-on system 13. fuel system 14. carbon dioxide add-on system 15. water add-on system

Embodiment

The present embodiment is the pilot system that a kind of test gas pollutes to supersonic combustor performance impact.

With Mach number 4, stagnation temperature is 880K, and the contrast test of pure air and dusty gas is example.Table 1 is the mole fraction of each component of supersonic combustor import.

Table 1 supersonic combustor inlet condition parameter

Test gas pollutes and is made up of pure air pilot system, dusty gas add-on system, fuel system, mixer, jet pipe, combustor test model the pilot system of supersonic combustor performance impact; Pure air pilot system comprises air source of the gas 1, main road air flow rate adjustment valve 2, electric resistance heater 3; Air source of the gas 1 sprays into electric resistance heater 3 by main road air flow rate adjustment valve 2 and heats, and successively by mixer 4, jet pipe 5, enters combustor test model 6.Tanks 8 in fuel system 13 is connected with combustor test model 6 by flow control valve; Fuel system 13 sprays by predetermined sequential control to combustor test model 6, burns, and carries out the supersonic combustor performance test of pure air incoming flow.

Dusty gas add-on system comprises water add-on system 15, carbon dioxide add-on system 14, oxygen add-on system 12, aqueous water in water piston cylinder 10 in water add-on system 15 is by piston press-in water heater 9, in water heater 9, aqueous water is heated to the water vapor of 400 ~ 750 DEG C, sprays into mixer 4; Carbon dioxide add-on system 14 is made up of carbon dioxide air source 11, flow control valve and annex, and carbon dioxide sprays into mixer 4 by flow control valve; Oxygen add-on system 12 is made up of oxygen source 7, flow control valve and annex, and oxygen sprays into mixer 4 by flow control valve, and mixer 4 is arranged between electric resistance heater 3 and jet pipe 5, and the oxygen mole fraction of mixer 4 exit gas is 21%; The oxygen that the carbon dioxide that mixer 4 is sprayed into by the water vapor that sprays into water add-on system 15 via the high enthalpy pure air of electric resistance heater 3, carbon dioxide add-on system 14, oxygen add-on system 12 spray into fully mixes, and enters into combustor test model 6 by jet pipe 5.Tanks 8 in fuel system 13 is connected with combustor test model 6 by flow control valve; Fuel system 13 sprays by predetermined sequential control to combustor test model 6, burns, and carries out the supersonic combustor performance test of dusty gas incoming flow.With Mach number 4, pure air and the air-polluting contrast test of Kerosene heater are the example brief description course of work:

The first step. the determination of trystate; During pure air test, require that the preset heating temperature value of setting electric resistance heater 3 is to 880K according to trystate, adjustment main road air flow rate adjustment valve 2, makes firing chamber import reach the flow of needs, and regulates fuel supply road pressure by fuel system 13; The supersonic combustor test of dusty gas, key is to produce the H meeting expection and require ₂o/CO ₂dusty gas.Employing exports in high enthalpy pure air at electric resistance heater quantitatively adds H ₂o, CO ₂component the mode of oxygenating carry out simulated combustion heating contaminated air.According to quality and energy conservation before and after oxygen content, mixing in test for contamination air, obtain:

$\frac{{\stackrel{\·}{m}}_{O_2}/W_{O_2}}{{\stackrel{\·}{m}}_{H_{2}O}/W_{H_{2}O}+{\stackrel{\·}{m}}_{C{O}_2}/W_{C{O}_2}+{\stackrel{\·}{m}}_{O_2}/W_{O_2}}=X_{O_2}=0.21---\left(1\right)$

$\frac{{\stackrel{\·}{m}}_{H_{2}O}/W_{H_{2}O}}{{\stackrel{\·}{m}}_{H_{2}O}/W_{H_{2}O}+{\stackrel{\·}{m}}_{C{O}_2}/W_{C{O}_2}+{\stackrel{\·}{m}}_{O_2}/W_{O_2}+{\stackrel{\·}{m}}_{\mathrm{Air}}/W_{\mathrm{Air}}}=X_{H_{2}O}---\left(2\right)$

$\frac{{\stackrel{\·}{m}}_{C{O}_2}/W_{{\mathrm{CO}}_2}}{{\stackrel{\·}{m}}_{H_{2}O}/W_{H_{2}O}+{\stackrel{\·}{m}}_{C{O}_2}/W_{C{O}_2}+{\stackrel{\·}{m}}_{O_2}/W_{O_2}+{\stackrel{\·}{m}}_{\mathrm{Air}}/W_{\mathrm{Air}}}=X_{{\mathrm{CO}}_2}---\left(3\right)$

${\stackrel{\·}{m}}_{H_{2}O}+{\stackrel{\·}{m}}_{H_{2}O}+{\stackrel{\·}{m}}_{O_2}+{\stackrel{\·}{m}}_{\mathrm{Air}}={\stackrel{\·}{m}}_{\mathrm{vit}}---\left(4\right)$

${\stackrel{\·}{m}}_{H_{2}O}h\left(T_{t,H_{2}O}\right)+{\stackrel{\·}{m}}_{{\mathrm{CO}}_2}h\left(T_{t,{\mathrm{CO}}_2}\right)+{\stackrel{\·}{m}}_{O_2}h\left(T_{t,O_2}\right)+{\stackrel{\·}{m}}_{\mathrm{Air}}{h}_{\mathrm{Air}}\left(T_{t,\mathrm{Air}}\right)={\stackrel{\·}{m}}_{\mathrm{vit}}h\left(T_{t,\mathrm{vit}}\right)---\left(5\right)$

In formula, X _h2Obe 3.00%, X _cO2be 3.00%, w, X and h represent mass rate, molecular weight, mole fraction and specific enthalpy respectively, subscript O2, air, H2O, CO2 and vit corresponding oxygen, resistance heated pure air, water component, carbon dioxide component and air-polluting parameter respectively, subscript t represents total parameter.According to energy conservation relation in formula (5), in order to produce the test for contamination air stagnation temperature T of satisfied pre-provisioning request _{t, vit}, can at T _{t, air}, T _{t, H2O}, T _{t, CO2}select one as regulated quantity in three.Consider accuracy requirement that is easy to operate and that control, in test, select regulating resistance heater outlet pure air stagnation temperature T _{t, air}realize contaminated air stagnation temperature T _{t, vit}control.Carbon dioxide is mixed into main flow in a gaseous form, and its temperature need ensure in filling process, do not occur condensation; The oxygen filled into is less, for room temperature is mixed into.Solve the parameter of each pollution components interpolation according to aforesaid equation, regulate the parameter of each add-on system to make its condition meeting test for contamination can start test.

Second step. in the temperature rise period, slowly open electric resistance heater upstream main road air flow rate adjustment valve 2, the regulating and control of intake air flow is completed by valve opening, when air mass flow reaches the minimum flow needed for electric resistance heater 3 clean boot, connect electric resistance heater 3 power supply, air flows through heating in electric resistance heater 3 and is heated up.

3rd step. pure air experimental stage, after electric resistance heater 3 outlet temperature and flow reach testing requirements and are constant, air-flow enters supersonic speed combustor test model 6 with predetermined pressure, temperature, Ma number and traffic flow after the equipment jet pipe 5 of main road, after setting up stable firing chamber inlet flow field, starting fluid supply control system 13, sprays to firing chamber according to predetermined sequential, burns.

4th step. dusty gas experimental stage, regulating resistance well heater 3 outlet temperature and flow to test for contamination require section and constant after, pollution components is sprayed in mixer 4, after setting up stable firing chamber inlet flow field, starting fluid supply system 13, sprays to firing chamber according to predetermined sequential, burns.

5th step. the off-test stage, after burning terminates, close electric resistance heater 3, and keep certain flow until after electric resistance heater 3 is cooled to set point of temperature, close main road air flow rate adjustment valve 2, fuel system 13, oxygen add-on system 12, carbon dioxide add-on system 14, water add-on system 15 successively, off-test.

6th step. according to the supersonic combustor test figure collected, analysis pollution components water and carbon dioxide are on the impact of supersonic combustor performance.

Claims (1)

1. the pilot system of a test gas pollution to supersonic combustor performance impact, it is characterized in that: comprise pure air pilot system, dusty gas add-on system, fuel system, mixer, jet pipe, combustor test model, pure air pilot system comprises air source of the gas, main road air flow rate adjustment valve, electric resistance heater, air source of the gas is connected with electric resistance heater by main road air flow rate adjustment valve, mixer is between electric resistance heater and jet pipe, and jet pipe is connected with combustor test model; Dusty gas add-on system comprises water add-on system, carbon dioxide add-on system, oxygen add-on system, water piston cylinder in water add-on system is connected with water heater, carbon dioxide air source in carbon dioxide add-on system is connected with flow control valve and annex, water add-on system is connected by pipeline and mixer with carbon dioxide add-on system, and the oxygen source in oxygen add-on system is connected with mixer by flow control valve and annex; Tanks in fuel system is connected with combustor test model by flow control valve; Test procedure is as follows:

(1) regulate main road air flow rate adjustment valve and electric resistance heater power, by air heat to 800 ~ 1000K, after the flow field in combustor test model is stable, opens fuel feed system, carry out the supersonic combustor performance test of pure air incoming flow;

(2) after completing pure air test, regulate main road air flow rate adjustment valve and electric resistance heater power, after electric resistance heater outlet air reaches required state, open dusty gas add-on system, high temperature air, carbon dioxide, water vapor, oxygen mix by a certain percentage in mixer, and the oxygen mole fraction of mixer outlet gas is 21%; Wherein, in water heater, aqueous water is heated to the water vapor of 400 ~ 750 DEG C, sprays into mixer; After flow field in combustor test model is stable, open fuel system, spray to combustor test model by predetermined sequential control, burn, carry out the supersonic combustor performance test of contaminated air incoming flow;

(3) according to the supersonic combustor test figure collected, analysis pollution components water and carbon dioxide are on the impact of supersonic combustor performance.