Oxygen-enriched afterburning cycle engine and performance deviation compensation method thereof

Abstract

The invention relates to an oxygen-enriched afterburning cycle engine, in particular to an oxygen-enriched afterburning cycle engine and a performance deviation compensation method thereof, and solves the problem that an existing engine performance deviation compensation method is difficult to ensure the qualified rate of an engine while meeting the performance precision. And the performance precision of the engine is difficult to accurately and effectively control. According to the performance deviation compensation method for the oxygen-enriched afterburning cycle engine, the mixing ratio regulator and the thrust regulator are arranged, the static simulation model of the engine is established, and the relation between thrust of the thrust regulator and the engine and the relation between the opening degree of the mixing ratio regulator and the mixing ratio of the engine are obtained through the static simulation model; and then the opening range of a thrust regulator and the opening range of a mixing ratio regulator are obtained according to the limit deviation range of the main interference factors so as to compensate the performance deviation of the engine, and therefore on the premise that system components are not replaced, targeted compensation of the performance deviation of the oxygen-enriched afterburning cycle engine is achieved.

Description

Technical Field

[0001] The invention relates to an oxygen-rich supplemental combustion cycle engine, and in particular to an oxygen-rich supplemental combustion cycle engine and a performance deviation compensation method thereof. Background Art

[0002] Liquid rocket engines can significantly improve their specific impulse performance by using an oxygen-rich regenerative cycle. However, the system of an oxygen-rich regenerative cycle engine is complex and has many components, which affect each other. When calculating the operating parameters, it is necessary to balance the deviations of the parameters of each component as much as possible so that the performance parameters of the oxygen-rich regenerative cycle engine meet user requirements.

[0003] The following problems usually exist when compensating for performance deviation of oxygen-rich combustion cycle engines:

[0004] 1) High engine performance requirements

[0005] When liquid rocket engines are used in launch vehicles or space vehicles, the engine's thrust, mixture ratio and other performance parameters have a significant impact on the rocket's carrying capacity or the vehicle's control accuracy. Therefore, the engine's performance parameters need to be strictly controlled. However, the existing engine performance deviation compensation method is difficult to ensure the engine's pass rate while meeting the performance requirements.

[0006] 2) The engine has many components and its performance is biased

[0007] Each component product has performance deviations due to processing, assembly and other processes. At the same time, there are deviations in the performance tests themselves. The existing engine performance deviation compensation method does not distinguish the degree of influence of each component on engine performance, making it difficult to achieve the purpose of accurately and effectively controlling engine performance parameters. Summary of the invention

[0008] The purpose of the present invention is to solve the technical problems that the existing engine performance deviation compensation method is difficult to ensure the engine's qualification rate while meeting performance requirements, and is difficult to accurately and effectively control engine performance parameters, and to provide an oxygen-rich regenerative cycle engine and its performance deviation compensation method.

[0009] The design concept of the present invention is:

[0010] An adjusting element is set on the flow path that significantly affects the engine performance. The steady-state parameter control of the adjusting element is high in precision and adjustable, which can compensate for the performance deviation of each component. At the same time, the engine performance can be calibrated through test runs, and the engine performance parameters can be further corrected without replacing components, thereby meeting the user's requirements for performance accuracy.

[0011] To achieve the above object, the technical solution adopted by the present invention is:

[0012] An oxygen-rich secondary combustion cycle engine comprises an oxidant pump, a primary fuel pump, a secondary fuel pump, a gas generator, a turbine and a thrust chamber;

[0013] The oxidant pump, the primary fuel pump, the secondary fuel pump and the turbine are coaxially arranged;

[0014] The inlet of the oxidant pump is the engine oxidant inlet, and the outlet is connected to the oxidant inlet of the gas generator through a pipeline;

[0015] The inlet of the primary fuel pump is the engine fuel inlet, and the outlet is connected to the cooling jacket fuel inlet of the thrust chamber and the inlet of the secondary fuel pump through pipelines;

[0016] The outlet of the secondary fuel pump is connected to the fuel inlet of the gas generator through a pipeline;

[0017] The gas outlet of the gas generator is connected to the inlet of the turbine through a pipeline, and the outlet of the turbine is connected to the gas inlet of the thrust chamber;

[0018] Its special features are:

[0019] Also includes a mixture ratio regulator and a thrust regulator;

[0020] The mixing ratio regulator is arranged on the pipeline between the fuel inlet of the thrust chamber cooling jacket and the outlet of the first-stage fuel pump;

[0021] The thrust regulator is arranged on the pipeline between the fuel inlet of the gas generator and the outlet of the secondary fuel pump.

[0022] The present invention also provides a method for compensating performance deviation of the above oxygen-rich supplemental combustion cycle engine, which is special in that it comprises the following steps:

[0023] Step 1: Establish a static simulation model according to the system parameters of the oxygen-rich supplementary combustion cycle engine; the system parameters include performance parameters;

[0024] Step 2: According to the static simulation model, the relationship between the opening of the thrust regulator, the opening of the mixture ratio regulator and the performance parameters is obtained; the performance parameters include engine thrust and engine mixture ratio;

[0025] Step 3: Based on the static simulation model, the interference factor of the oxygen-rich combustion cycle engine is taken as the independent variable and the performance parameter is taken as the dependent variable to obtain the sensitivity equation;

[0026] Step 4: non-dimensionalize the performance parameters and interference factors to obtain dimensionless quantities, and then substitute the dimensionless quantities into the sensitivity equation to obtain the dimensionless sensitivity of the performance parameters to the interference factors;

[0027] Step 5: Compare the dimensionless sensitivity of the performance parameters to the interference factors, and record the interference factor corresponding to the dimensionless sensitivity with a large value as the main interference factor;

[0028] Step 6: Obtain the limit deviation range of the main interference factors according to the production data, test data and usage requirements, and then calculate the deviation range of the performance parameters according to the limit deviation range of the main interference factors;

[0029] Step 7: According to the relationship between the opening of the thrust regulator and the engine thrust, the relationship between the opening of the mixture ratio regulator and the engine mixture ratio obtained in step 2, and the deviation range of the performance parameters obtained in step 6, the opening ranges of the thrust regulator and the mixture ratio regulator required to compensate for the deviation range of the performance parameters are calculated, and then the openings of the mixture ratio regulator and the thrust regulator are adjusted to compensate for the performance deviation, thereby completing the performance deviation compensation of the oxygen-rich staged combustion cycle engine.

[0030] Furthermore, in step 1, the performance parameters include engine thrust and engine mixture ratio, and the static simulation model is:

[0031] F=(q mo +q mf )·I+(p e -p a )·A e

[0032]

[0033] P t =P po +P pf

[0034] p epo =p ipo +Δp po

[0035]

[0036] p epf1 =p ipf1 +Δp pf1

[0037]

[0038] o epf2 =p epf1 +Δp pf2

[0039] K=q mo / q mf

[0040] Where F is the engine thrust, qmo is the oxidant flow rate at the engine oxidant inlet, q mf is the fuel flow rate at the engine fuel inlet, I is the engine specific impulse, p e is the nozzle outlet pressure, p a is the environmental pressure, A e is the nozzle outlet area; q mf =q mfc +q mpf2 ,q mfc is the fuel flow rate in the thrust chamber, is the mixture ratio regulator opening α thr Function of q mpf2 is the fuel flow rate of the secondary fuel pump, is the thrust regulator opening α tj Function of

[0041] P po is the power of the oxidant pump, Δp po is the head of the oxidant pump, ρ po is the propellant density of the oxidizer pump, η po is the efficiency of the oxidant pump; n is the speed of the turbine, a po , b po 、c po is the fitting coefficient of the oxidant pump head curve, obtained from the oxidant pump hydraulic test;

[0042] P pf is the total power of the primary fuel pump and the secondary fuel pump, Δp pf1 is the head of the first-stage fuel pump, ρ pf1 is the propellant density of the first stage fuel pump, η pf1 is the efficiency of the primary fuel pump, Δp pf2 is the head of the secondary fuel pump, q mof2 is the fuel flow rate of the secondary fuel pump, ρ pf2 is the propellant density of the fuel secondary pump, η pf2 The efficiency of the secondary fuel pump; a pf1 , b pf1 、c pf1 is the fitting coefficient of the fuel primary pump head curve, obtained from the fuel primary pump hydraulic test; a pf2 , b pf2 、c pf2 is the fitting coefficient of the fuel secondary pump head curve, obtained from the fuel secondary pump hydraulic test;

[0043] q t is the power of the turbine, η t is the efficiency of the turbine, q mt are the oxidant and fuel flow rates entering the turbine, qmt =q mo +q mpf2 , k gg is the constant entropy index of the turbine gas, R gg is the turbine gas constant, T gg is the turbine inlet gas temperature, p et is the outlet pressure of the turbine, p it is the turbine inlet pressure; p c is the pressure in the thrust chamber, ξ etg is the turbine outlet gas flow resistance coefficient, T et is the turbine outlet gas temperature,

[0044] p epo is the outlet pressure of the oxidant pump, p ipo is the pressure of the engine oxidant inlet, p gg is the pressure of the gas generator, ξ ggo is the oxidant path flow resistance coefficient of the gas generator, ρ epo is the oxidant density at the outlet of the oxidant pump; ξ ith is the turbine inlet gas path flow resistance coefficient;

[0045] p epf1 is the outlet pressure of the first-stage fuel pump, p ipf1 is the pressure of the engine fuel inlet, ξ fc is the total flow resistance coefficient of the fuel supply path of the thrust chamber, ρ epf1 is the fuel density at the outlet of the first-stage fuel pump; p c =(q mo +q mf )×C * / (π×D 2 / 4), C * is the characteristic velocity of the thrust chamber gas, which is determined by the thrust chamber pressure, engine mixture ratio and combustion efficiency Determine, D is the throat diameter of the thrust chamber; ξ fc =ξ thr (α thr )+ξ tc ,ξ thr is the flow resistance coefficient of the mixing ratio regulator (2), and is its opening α thr function, ξ tc is the flow resistance coefficient of the cooling channel and injector of the thrust chamber;

[0046] p epf2 is the outlet pressure of the secondary fuel pump;

[0047] K is the engine mixture ratio.

[0048] Furthermore, in step 3, the sensitivity equation is:

[0049]

[0050] Among them, (h1,h2,…,h m )=H, is the interference factor of the oxygen-rich combustion cycle engine, including internal interference factors and external interference factors, the internal interference factors include the structural parameters and design parameters of the oxygen-rich combustion cycle engine, and the external interference factors include the engine oxidant inlet pressure, the engine fuel inlet pressure, the engine oxidant inlet temperature and the engine fuel inlet temperature;

[0051] (x1,x2,…,x n ) = X, which is the performance parameter of the oxygen-rich combustion cycle engine;

[0052] Indicates performance parameter x i For interference factors j Sensitivity, 1≤i≤n, 1≤j≤m.

[0053] Furthermore, step 4 is specifically as follows:

[0054] 4.1. Obtain the rated design values ​​of the performance parameters and interference factors of the oxygen-rich combustion cycle engine;

[0055] 4.2. Calculate the dimensionless quantities of performance parameters and interference factors respectively according to the following formulas:

[0056]

[0057] Among them, X represents the actual value, X o Indicates the rated design value, represents a dimensionless quantity;

[0058] 4.3. Substitute the dimensionless quantities of performance parameters and interference factors into the sensitivity equation to obtain the dimensionless sensitivity of performance parameters to interference factors.

[0059] Further, in step 6, the deviation range of the performance parameter is calculated by the following formula:

[0060]

[0061]

[0062] Wherein, ΔF represents the deviation range of engine thrust, ΔK represents the deviation range of engine mixture ratio, Δh1, Δh2, ..., Δh m Indicates the limit deviation range of the main interference factors, h1 o 、h2o ,...,h m o Indicates the rated design value of the main interference factor, The dimensionless quantity representing the main interference factor, F o Indicates the rated design value of the engine thrust, K o Indicates the rated design value of the engine mixture ratio. A dimensionless quantity representing the engine thrust, A dimensionless quantity representing the engine's mixture ratio.

[0063] Compared with the prior art, the present invention has the following beneficial technical effects:

[0064] 1. The performance deviation compensation method of the oxygen-rich staged combustion cycle engine provided by the present invention is to set a thrust regulator on the fuel path of the gas generator to stabilize or change the flow rate of the path, and to set a mixture ratio regulator on the fuel path of the thrust chamber to change the flow resistance of the fuel path of the thrust chamber, so as to stably adjust the engine thrust and the engine mixture ratio, and to compensate for the performance deviation in a targeted manner. Under the premise of not replacing system components, the engine performance parameters can be corrected, which can not only meet the performance requirements, but also ensure the qualified rate of the engine;

[0065] 2. In the performance deviation compensation method of the oxygen-rich regenerative cycle engine provided by the present invention, by establishing a static simulation model of the oxygen-rich regenerative cycle engine, the relationship between the performance deviations of the engine thrust and the mixture ratio and the thrust regulator opening range and the mixture ratio regulator opening range is obtained, and the deviation caused by the interference factor is compensated by adjusting the thrust regulator and the mixture ratio regulator;

[0066] 3. In the performance deviation compensation method of the oxygen-rich regenerative cycle engine provided by the present invention, the dimensionless sensitivity of the performance parameters to the interference factors is obtained by making the interference factors and performance parameters dimensionless, so as to evaluate the influence of the interference factors on the engine performance, thereby effectively determining the interference factors that have a greater impact on the engine performance and realizing precise control of the engine performance parameters. BRIEF DESCRIPTION OF THE DRAWINGS

[0067] Figure 1 It is a schematic structural diagram of an oxygen-rich supplementary combustion cycle engine according to an embodiment of the present invention;

[0068] The following are the descriptions of the reference numerals:

[0069] 1-thrust chamber, 2-mixture ratio regulator, 3-thrust regulator, 4-gas generator, 5-turbine, 6-oxidizer pump, 7-first fuel pump, 8-second fuel pump. DETAILED DESCRIPTION

[0070] The oxygen-rich combustion cycle engine and its performance deviation compensation method proposed by the present invention are further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood by those skilled in the art that these embodiments are only used to explain the technical principles of the present invention and are not intended to limit the scope of protection of the present invention.

[0071] An oxygen-rich combustion cycle engine, such as Figure 1 The system comprises an oxidant pump 6, a primary fuel pump 7, a secondary fuel pump 8, a gas generator 4, a turbine 5 and a thrust chamber 1, as well as a mixture ratio regulator 2 and a thrust regulator 3.

[0072] The oxidant pump 6, the primary fuel pump 7, the secondary fuel pump 8 and the turbine 5 are coaxially arranged. The inlet of the oxidant pump 6 is the engine oxidant inlet, and the outlet is connected to the oxidant inlet of the gas generator 4 through a pipeline. The inlet of the primary fuel pump 7 is the engine fuel inlet, and the outlet is connected to the cooling jacket fuel inlet of the thrust chamber 1 and the inlet of the secondary fuel pump 8 through pipelines. The outlet of the secondary fuel pump 8 is connected to the fuel inlet of the gas generator 4 through a pipeline. The gas outlet of the gas generator 4 is connected to the inlet of the turbine 5 through a pipeline, and the outlet of the turbine 5 is connected to the gas inlet of the thrust chamber 1. The mixture ratio regulator 2 is arranged on the pipeline between the fuel inlet of the cooling jacket of the thrust chamber 1 and the outlet of the primary fuel pump 7, and the thrust regulator 3 is arranged on the pipeline between the fuel inlet of the gas generator 4 and the outlet of the secondary fuel pump 8. The steady-state parameter control accuracy of the mixture ratio regulator 2 and the thrust regulator 3 is high and adjustable, and the performance of the engine can be calibrated through test runs to compensate for the performance deviations of various components of the system.

[0073] The present invention also provides a method for compensating performance deviation of an oxygen-rich supplemental combustion cycle engine, using the above-mentioned oxygen-rich supplemental combustion cycle engine, comprising the following steps:

[0074] Step 1: Establish a static simulation model based on the system parameters of the oxygen-rich combustion cycle engine, wherein the system parameters include performance parameters.

[0075] The static simulation model is as follows:

[0076] F=(q mo +q mf )·I+(p e -p a )·A e

[0077]

[0078] P t =P po +P pf

[0079] o epo =pipo +Δp po

[0080]

[0081] p epf1 =p ipf1 +Δp pf1

[0082]

[0083] o epf2 =p epf1 +Δp pf2

[0084] K=q mo / q mf

[0085] Where F is the engine thrust, q mo is the oxidant flow rate at the engine oxidant inlet, q mf is the fuel flow rate at the engine fuel inlet, I is the engine specific impulse, p e is the nozzle outlet pressure, p a is the environmental pressure, A e is the nozzle outlet area; q mf =q mfc +q mpf2 ,q mfc is the fuel flow rate of thrust chamber 1, is the opening degree α of mixture ratio regulator 2 thr Function of q mpf2 is the fuel flow rate of the secondary fuel pump 8, is the opening degree α of the thrust regulator 3 tj Function of

[0086] P po is the power of the oxidant pump 6, Δp po is the head of the oxidant pump 6, ρ po is the propellant density of the oxidizer pump 6, η po is the efficiency of the oxidant pump 6; n is the rotation speed of turbine 5, a po , b po 、c po is the fitting coefficient of the head curve of the oxidant pump 6, obtained from the hydraulic test of the oxidant pump 6;

[0087] P pf is the total power of the primary fuel pump 7 and the secondary fuel pump 8, Δp pf1 is the head of the fuel primary pump 7, ρ pf1 is the propellant density of the fuel primary pump 7, η pf1 is the efficiency of the primary fuel pump 7, Δppf2 is the head of the fuel secondary pump 8, q mpf2 is the fuel flow rate of the secondary fuel pump 8, ρ pf2 is the propellant density of the fuel secondary pump 7, η pf2 The efficiency of the secondary fuel pump; a pf1 , b pf1 、c pf1 is the fitting coefficient of the head curve of the fuel primary pump 7, obtained from the hydraulic test of the fuel primary pump 7; a pf2 , b pf2 、c pf2 is the fitting coefficient of the lift curve of the fuel secondary pump 8, obtained from the hydraulic test of the fuel secondary pump 8;

[0088] P t is the power of turbine 5, η t is the efficiency of turbine 5, q mt are the oxidant and fuel flow rates entering turbine 5, q mt =q mo +q mpf2 , k gg is the constant entropy index of the gas of turbine 5, R gg is the gas constant of turbine 5, T gg is the inlet gas temperature of turbine 5, p et is the outlet pressure of turbine 5, p it is the inlet pressure of turbine 5; p c is the pressure in thrust chamber 1, ξ etg is the outlet gas flow resistance coefficient of turbine 5, T et is the outlet gas temperature of turbine 5,

[0089] p epo is the outlet pressure of the oxidant pump 6, p ipo is the pressure of the engine oxidant inlet, p gg is the pressure of the gas generator 4, ξ ggo is the oxidant path flow resistance coefficient of the gas generator 4, ρ epo is the oxidant density at the outlet of the oxidant pump 6; ξ itg is the inlet gas path flow resistance coefficient of turbine 5;

[0090] p epf1 is the outlet pressure of the fuel primary pump 7, p ipf1 is the pressure of the engine fuel inlet, ξ fcis the total flow resistance coefficient of the fuel supply path of thrust chamber 1, ρ epf1 is the fuel density at the outlet of the fuel primary pump 7; p c =(q mo +q mf )×C * / (π×D 2 / 4), C * is the characteristic velocity of the gas in thrust chamber 1, which is determined by the chamber pressure of thrust chamber 1, engine mixture ratio and combustion efficiency Determine, D is the throat diameter of the thrust chamber 1; ξ fc =ξ thr (α thr )+ξ tc ,ξ thr is the flow resistance coefficient of the mixing ratio regulator 2, and is its opening α thr function, ξ tc is the flow resistance coefficient of the cooling channel and injector of the thrust chamber 1;

[0091] p epf2 is the outlet pressure of the secondary fuel pump 8;

[0092] K is the engine mixture ratio.

[0093] The performance parameters in the static simulation model are hydraulic test values ​​or statistical characteristics. The correctness of the static simulation model can be verified through the test data of the engine.

[0094] Step 2: According to the static simulation model, the relationship between the opening of the thrust regulator 3, the opening of the mixture ratio regulator 2 and the performance parameters is obtained, which are the relationship between the opening of the thrust regulator 3 and the engine thrust, and the relationship between the opening of the mixture ratio regulator 2 and the engine mixture ratio.

[0095] Step 3: Based on the static simulation model, the interference factors of the oxygen-rich combustion cycle engine are used as independent variables, and the performance parameters are used as dependent variables to obtain the sensitivity equation. The interference factors include internal interference factors and external interference factors. The internal interference factors include the structural parameters and design parameters of the oxygen-rich combustion cycle engine, the head curve fitting coefficient a of the oxidant pump 6, and the external interference factors. po , b po 、c po , the oxidant path flow resistance coefficient ξ of the gas generator 4 gg Etc. External interference factors include engine oxidant inlet pressure, engine fuel inlet pressure, engine oxidant inlet temperature and engine fuel inlet temperature.

[0096] The sensitivity equation is as follows:

[0097]

[0098] Among them, (h1,h2,…,h m ) = H, which is the interference factor of the oxygen-rich combustion cycle engine;

[0099] (x1,x2,…,x n ) = X, which is the performance parameter of the oxygen-rich combustion cycle engine;

[0100] Indicates performance parameter x i For interference factors j Sensitivity, 1≤i≤n, 1≤j≤m.

[0101] Step 4: Non-dimensionalize the performance parameters and interference factors to obtain dimensionless quantities, and then substitute the dimensionless quantities into the sensitivity equation to obtain the dimensionless sensitivity of the performance parameters to the interference factors. Specifically:

[0102] 4.1. Obtain the rated design values ​​of the performance parameters and interference factors of the oxygen-rich secondary combustion cycle engine.

[0103] 4.2. Calculate the dimensionless quantities of performance parameters and interference factors respectively according to the following formulas:

[0104]

[0105] Among them, X represents the actual value, X o Indicates the rated design value, Represents a dimensionless quantity.

[0106] For example, the actual value of engine thrust Actual value of the engine mixture ratio Actual value of the throat diameter of thrust chamber 1

[0107] 4.3. Substitute the dimensionless quantities of the performance parameters of each component of the system and the interference factors into the sensitivity equation to obtain the dimensionless sensitivity of the performance parameters of each component of the system to the interference factors.

[0108] Dimensionlessization can compare the significance of the impact of interference factors on performance parameters and then find out the main interference factors. Therefore, it is necessary to introduce the characteristic values ​​of each variable, namely the rated parameters, including the rated design values ​​of the interference factors and the rated values ​​of the performance parameters of each component of the system.

[0109] Step 5: Compare the dimensionless sensitivities of the performance parameters to the interference factors, and record the interference factors corresponding to the larger dimensionless sensitivities as the main interference factors.

[0110] Step 6: Obtain the limit deviation range of the main interference factors based on the production data, test data and usage requirements, and then calculate the deviation range of the performance parameters based on the limit deviation range of the main interference factors.

[0111] The deviation range of the performance parameters is calculated by the following formula:

[0112]

[0113] Wherein, ΔF represents the deviation range of engine thrust, ΔK represents the deviation range of engine mixture ratio, Δh1, Δh2, ..., Δh m Indicates the limit deviation range of the main interference factors, h1 o 、h2 o ,...,h m o Indicates the rated design value of the main interference factor, The dimensionless quantity representing the main interference factor, F o Indicates the rated design value of the engine thrust, K o Indicates the rated design value of the engine mixture ratio. A dimensionless quantity representing the engine thrust, A dimensionless quantity representing the engine's mixture ratio.

[0114] Step 7: According to the relationship between the opening of the thrust regulator 3 and the engine thrust, the relationship between the opening of the mixture ratio regulator 2 and the engine mixture ratio obtained in step 2, and the deviation range of the performance parameters obtained in step 6, the opening ranges of the thrust regulator 3 and the mixture ratio regulator 2 required to compensate for the performance parameter deviation range are calculated, and then the openings of the mixture ratio regulator 2 and the thrust regulator 3 are adjusted to compensate for the performance deviation, thereby completing the performance deviation compensation of the oxygen-rich staged combustion cycle engine.

[0115] The performance deviation compensation method of the oxygen-rich regenerative cycle engine proposed in the present invention can be applied in the development process of the oxygen-rich regenerative cycle engine with normal temperature propellant, by arranging a thrust regulator and a mixture ratio regulator in the oxygen-rich regenerative cycle engine, and establishing a static simulation model of the engine, the relationship between the thrust regulator and the engine thrust, and the relationship between the mixture ratio regulator opening and the engine mixture ratio is obtained through the static simulation model, the thrust regulator opening range and the mixture ratio regulator opening range are obtained through the limit deviation range of the main interference factors, and the performance deviation of the engine is compensated, thereby realizing targeted compensation of the performance deviation without replacing system components.

Claims

1. An oxygen-rich secondary combustion cycle engine, comprising an oxidant pump (6), a primary fuel pump (7), a secondary fuel pump (8), a gas generator (4), a turbine (5) and a thrust chamber (1); The oxidant pump (6), the primary fuel pump (7), the secondary fuel pump (8) and the turbine (5) are coaxially arranged; The inlet of the oxidant pump (6) is the engine oxidant inlet, and the outlet is connected to the oxidant inlet of the gas generator (4) through a pipeline; The inlet of the primary fuel pump (7) is the engine fuel inlet, and the outlet is connected to the cooling jacket fuel inlet of the thrust chamber (1) and the inlet of the secondary fuel pump (8) through pipelines; The outlet of the secondary fuel pump (8) is connected to the fuel inlet of the gas generator (4) through a pipeline; The gas outlet of the gas generator (4) is connected to the inlet of the turbine (5) through a pipeline, and the outlet of the turbine (5) is connected to the gas inlet of the thrust chamber (1); Features: It also includes a mixture ratio regulator (2) and a thrust regulator (3); The mixing ratio regulator (2) is arranged on a pipeline between the fuel inlet of the cooling jacket of the thrust chamber (1) and the outlet of the primary fuel pump (7); The thrust regulator (3) is arranged on a pipeline between the fuel inlet of the gas generator (4) and the outlet of the secondary fuel pump (8).

2. A method for compensating performance deviation of an oxygen-rich combustion cycle engine as claimed in claim 1, characterized in that: The following steps are involved: Step 1: Establish a static simulation model according to the system parameters of the oxygen-rich supplementary combustion cycle engine; the system parameters include performance parameters; Step 2: According to the static simulation model, the relationship between the opening of the thrust regulator (3), the opening of the mixture ratio regulator (2) and the performance parameters is obtained; Step 3: Based on the static simulation model, the interference factor of the oxygen-rich combustion cycle engine is taken as the independent variable and the performance parameter is taken as the dependent variable to obtain the sensitivity equation; Step 4: non-dimensionalize the performance parameters and interference factors to obtain dimensionless quantities, and then substitute the dimensionless quantities into the sensitivity equation to obtain the dimensionless sensitivity of the performance parameters to the interference factors; Step 5: Compare the dimensionless sensitivity of the performance parameters to the interference factors, and record the interference factor corresponding to the dimensionless sensitivity with a large value as the main interference factor; Step 6: Obtain the limit deviation range of the main interference factors according to the production data, test data and usage requirements, and then calculate the deviation range of the performance parameters according to the limit deviation range of the main interference factors; Step 7: Based on the relationship between the opening of the thrust regulator (3) and the opening of the mixture ratio regulator (2) and the performance parameter obtained in step 2, and the deviation range of the performance parameter obtained in step 6, the opening range of the thrust regulator (3) and the mixture ratio regulator (2) required to compensate for the deviation range of the performance parameter is calculated, and then the opening of the mixture ratio regulator (2) and the thrust regulator (3) are adjusted to compensate for the performance deviation, thereby completing the performance deviation compensation of the oxygen-rich staged combustion cycle engine.

3. The performance deviation compensation method of an oxygen-rich supplemental combustion cycle engine according to claim 2, characterized in that: In step 1, the performance parameters include engine thrust and engine mixture ratio, and the static simulation model is: F=(q mo +q mf )·I+(p e -p a )·A e P t =P po +P pf p epo =p ipo +Δp po p epf1 =p ipf1 +Δp pf1 p epf2 =p epf1 +Δp pf2 K=q mo / q mf Where F is the engine thrust, q mo is the oxidant flow rate at the engine oxidant inlet, q mf is the fuel flow rate at the engine fuel inlet, I is the engine specific impulse, p e is the nozzle outlet pressure, p a is the environmental pressure, A e is the nozzle outlet area; q mf =q mfc +q mpf2 ,q mfc is the fuel flow rate of the thrust chamber (1), is the opening α of the mixture ratio regulator (2) thr Function of q mpf2 is the fuel flow rate of the secondary fuel pump (8), is the opening degree α of the thrust regulator (3) tj Function of P po is the power of the oxidant pump (6), Δp po is the head of the oxidant pump (6), ρ po is the propellant density of the oxidizer pump (6), η po is the efficiency of the oxidant pump (6); n is the speed of the turbine (5), a po , b po 、c po is the fitting coefficient of the head curve of the oxidant pump (6), obtained from the hydraulic test of the oxidant pump (6); P pf is the total power of the primary fuel pump (7) and the secondary fuel pump (8), Δp pf1 is the head of the primary fuel pump (7), ρ pf1 is the propellant density of the fuel primary pump (7), η pf1 is the efficiency of the primary fuel pump (7), Δp pf2 is the head of the secondary fuel pump (8), q mpf2 is the fuel flow rate of the secondary fuel pump (8), ρ pf2 is the propellant density of the fuel secondary pump (7), η pf2 is the efficiency of the fuel secondary pump (7); a pf1 , b pf1 、c pf1 is the fitting coefficient of the head curve of the primary fuel pump (7), obtained from the hydraulic test of the primary fuel pump (7); a pf2 , b pf2 、c pf2 is the fitting coefficient of the head curve of the fuel secondary pump (8), obtained from the hydraulic test of the fuel secondary pump (8); P t is the power of turbine (5), η t is the efficiency of turbine (5), q mt are the oxidant and fuel flow rates entering the turbine (5), q mt =q mo +q mpf2 , k gg is the constant entropy index of the gas in the turbine (5), R gg is the gas constant of the turbine (5), T gg is the inlet gas temperature of the turbine (5), p et is the outlet pressure of turbine (5), p it is the inlet pressure of the turbine (5); p c is the pressure in the thrust chamber (1), ξ etg is the outlet gas flow resistance coefficient of the turbine (5), T et is the outlet gas temperature of the turbine (5), p epo is the outlet pressure of the oxidant pump (6), p ipo is the pressure of the engine oxidant inlet, p gg is the pressure of the gas generator (4), ξ ggo is the flow resistance coefficient of the oxidant path of the gas generator (4), ρ epo is the oxidant density at the outlet of the oxidant pump (6); ξ itg is the inlet gas path flow resistance coefficient of the turbine (5); p epf1 is the outlet pressure of the primary fuel pump (7), p ipf1 is the pressure of the engine fuel inlet, ξ fc is the total flow resistance coefficient of the fuel supply path of the thrust chamber (1), ρ epf1 is the fuel density at the outlet of the first fuel pump (7); p c =(q mo +q mf )×C * / (π×D 2 / 4), C * is the characteristic velocity of the gas in the thrust chamber (1), which is determined by the chamber pressure of the thrust chamber (1), the engine mixture ratio and the combustion efficiency Determine, D is the throat diameter of the thrust chamber (1); ξ fc =ξ thr (α thr )+ξ tc ,ξ thr is the flow resistance coefficient of the mixing ratio regulator (2), and is its opening α thr function, ξ tc is the flow resistance coefficient of the cooling channel and injector of the thrust chamber (1); p epf2 is the outlet pressure of the secondary fuel pump (8); K is the engine mixture ratio.

4. The performance deviation compensation method of an oxygen-rich supplemental combustion cycle engine according to claim 3, characterized in that: In step 3, the sensitivity equation is: Among them, (h1,h2,…,h m )=H, represents the interference factors of the oxygen-rich combustion cycle engine, including internal interference factors and external interference factors, the internal interference factors include the structural parameters and design parameters of the oxygen-rich combustion cycle engine, and the external interference factors include the engine oxidant inlet pressure, the engine fuel inlet pressure, the engine oxidant inlet temperature and the engine fuel inlet temperature; (x1,x2,…,x n )=X, representing the performance parameters of the oxygen-rich combustion cycle engine; Indicates performance parameter x i The interference factor h j Sensitivity, 1≤i≤n, 1≤j≤m.

5. The performance deviation compensation method of an oxygen-rich supplemental combustion cycle engine according to claim 4, characterized in that: Step 4 is as follows: 4.

1. Obtain the rated design values ​​of the performance parameters and interference factors of the oxygen-rich combustion cycle engine; 4.

2. Calculate the dimensionless quantities of performance parameters and interference factors respectively according to the following formulas: Among them, X represents the actual value, X o Indicates the rated design value, represents a dimensionless quantity; 4.

3. Substitute the dimensionless quantities of performance parameters and interference factors into the sensitivity equation to obtain the dimensionless sensitivity of performance parameters to interference factors.

6. The performance deviation compensation method of an oxygen-rich supplemental combustion cycle engine according to claim 5, characterized in that: In step 6, the deviation range of the performance parameter is calculated by the following formula: Wherein, ΔF represents the deviation range of engine thrust, ΔK represents the deviation range of engine mixture ratio, Δh1, Δh2, ..., Δh m Indicates the limit deviation range of the main interference factors, h1 o 、h2 o ,...,h m o Indicates the rated design value of the main interference factor, The dimensionless quantity representing the main interference factor, F o Indicates the rated design value of the engine thrust, K o Indicates the rated design value of the engine mixture ratio. A dimensionless quantity representing the engine thrust, A dimensionless quantity representing the engine's mixture ratio.

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