CN114722743B - One-dimensional performance estimation method of scramjet engine based on combustion chamber chemical balance - Google Patents
One-dimensional performance estimation method of scramjet engine based on combustion chamber chemical balance Download PDFInfo
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Abstract
The invention provides a scramjet engine one-dimensional performance estimation method based on combustion chamber chemical balance, which is characterized in that flight condition parameters are given, fuel types are selected, basic geometric dimensions of the scramjet engine are selected, physical quantities of the scramjet engine along the way are solved through a one-dimensional calculation method, flow channel parameters of all sections are further obtained, and further, the total performance parameters of the scramjet engine such as specific impulse, specific thrust and the like can be solved through momentum theorem, so that the purpose of scramjet engine performance estimation is achieved. The invention can comprehensively consider the influence of factors such as wall friction of the engine, fuel mass addition, chemical balance heat release, specific geometric dimension of the engine and the like on the performance of the scramjet engine. Compared with a zero-dimensional model, the estimation error is greatly reduced.
Description
Technical Field
The invention belongs to the technical field of scramjet engines, and particularly relates to a scramjet engine one-dimensional performance estimation method based on combustion chamber chemical balance.
Background
The research of the scramjet belongs to the field of national defense science and technology frontier, and is one of ideal power devices of hypersonic cruise missiles. The structure schematic diagram of the scramjet engine is shown in fig. 2, and the scramjet engine mainly comprises an air inlet channel, an isolation section, a supersonic combustion chamber and a tail nozzle. The compression process is realized by an air inlet channel which is responsible for compressing high-speed incoming flow. The combustion process is realized by an isolation section and the supersonic combustion chamber, and the isolation section is mainly used for isolating the influence of the back pressure of the supersonic combustion chamber on the air inlet channel; the specific configuration of the supersonic combustor consists of two expansion sections, wherein the first expansion section is mainly used for realizing a fuel injection (additive) process, and the second expansion section is used for realizing mixing and heat release processes of fuel in the supersonic combustor. The heat release process in the supersonic combustor solves the chemical equilibrium state using the minimum gibbs free energy assumption. The expansion process is mainly realized by the supersonic velocity spray pipe, and the spray pipe is mainly used for expanding and working combustion products with high temperature and high pressure so as to generate thrust.
The scramjet engine test comprises a ground direct connection test, a free jet test and a flight test, the test development has the characteristics of high cost, high difficulty and the like, and the three-dimensional high-precision numerical simulation has the characteristics of long calculation period and the like. Based on the situation, the method for estimating the one-dimensional performance of the scramjet engine can quickly analyze the performance limit of one engine configuration, and the calculation time can be shortened to the second order. Therefore, a basic judgment can be made on the performance parameters of the engine through one-dimensional performance estimation before tests and high-precision simulation are carried out, and therefore the time and the economic cost of the optimal design of the scramjet engine can be effectively reduced.
The existing performance estimation method for the scramjet engine mainly comprises zero-dimensional performance estimation and one-dimensional performance estimation. The heat release process of zero-dimensional property estimation usually adopts an isobaric assumption, an equal-area assumption or an equal-Mach number assumption, which do not accord with the actual working process of the scramjet engine. In addition, zero-dimensional performance estimates are often calculated for ease, ignoring the effects of friction and additives, which must also be considered in practical scramjet engines.
Due to the reasons, the zero-dimensional calculation method brings large errors to the performance estimation of the scramjet engine. The existing heating process with one-dimensional performance estimation usually adopts finite rate chemical reaction to calculate the heating quantity or directly uses the fuel calorific value to calculate the heating quantity. The heating process based on the finite-rate chemical reaction considers the kinetics of the chemical reaction, but needs to call a detailed chemical reaction mechanism for calculation, and the time is relatively long; the heating process based on calculating the amount of heating using the fuel heating value does not take into account the combustion product dissociation process in the combustion process, which can produce large errors for high mach number performance evaluations.
Disclosure of Invention
The invention aims to provide a one-dimensional performance estimation method of a scramjet based on chemical balance of a combustion chamber, which can directly and quickly calculate performance parameters such as specific thrust, specific impulse and the like of the scramjet and various physical quantities along the path.
In order to achieve the technical purpose, the technical scheme provided by the invention is as follows:
in one aspect, the invention provides a method for estimating one-dimensional performance of a scramjet engine based on chemical balance of a combustion chamber, which comprises the following steps:
(S1) determining flow parameters of an inlet section of an air inlet channel, and solving the flow parameters of an outlet section of the air inlet channel;
(S2) calculating the heat release amount of each axial motion step in the flow combustion process based on the chemical balance of the combustion chamber by combining a given fuel type and a given flight equivalence ratio according to a differential equation of a one-dimensional fluid control equation, so as to obtain flow parameters of each position along the path of the combustion chamber by space propulsion solution;
(S3) keeping the total enthalpy of combustion products unchanged in the expansion process of the tail nozzle, simplifying the expansion process of the tail nozzle into a variable-sectional-area friction pipeline flow process without energy addition according to given geometric parameters of the tail nozzle, constructing a fluid control differential equation in the tail nozzle, and solving flow parameters of all positions of the tail nozzle;
and (S4) solving the overall performance parameters of the scramjet.
Further, as a preferred embodiment, a flow parameter of an inlet cross section of an air inlet channel is determined, the method comprising:
the method comprises the following steps of (1) giving the flight altitude, the flight Mach number and the inflow flow of the scramjet engine, and the static temperature, the static pressure and the density of the inlet section of an air inlet channel;
and determining flow parameters of the inlet section of the air inlet by combining a mass conservation equation, an adiabatic assumption, a sound velocity formula, a speed and Mach number relational expression and an isentropic relational expression at the inlet section of the air inlet, wherein the flow parameters comprise the total temperature, the total pressure, the speed and the inlet section area of the inlet section of the air inlet.
Further, as a preferred embodiment, (S1) in the known adiabatic compression efficiency
Mach number ratio of inlet/outlet of inlet duct
And under the condition, determining the flow parameters of the outlet section of the air inlet channel by combining the adiabatic assumption, the mass conservation equation and the state equation at the outlet section of the air inlet channel.
Further, as a preferable embodiment, (S1) the adiabatic compression efficiency is set
0.9, ratio of Mach number of outlet/inlet of air inlet duct
Is 0.4.
Further, as a preferred embodiment, (S2) in axial movement step lengthdxDividing an isolation section between an inlet section of the isolation section of the scramjet engine and an outlet section of the combustion chamber and the combustion chamber into a plurality of one-dimensional control bodies, constructing a differential equation of a one-dimensional fluid control equation of the one-dimensional control bodies, and solving the differential equation of the one-dimensional fluid control equation of the constructed one-dimensional control bodies to obtain flow parameters of each part along the way from the isolation section to the combustion chamber.
Further, as a preferred embodiment, (S2) there is no mass addition and chemical heat release in the isolation section, the isolation section is regarded as a friction pipeline with a uniform cross section, only the friction resistance between the fluid and the wall surface is considered in the isolation section, for any one-dimensional control body of the isolation section, the influence coefficient of each factor of the one-dimensional control body is expressed as a mathematical expression about mach number and specific heat ratio, a differential equation of a one-dimensional fluid control equation of each one-dimensional control body in the isolation section is constructed, and under the condition that the inlet condition and the heat release rule of the isolation section are known, the on-way flow parameters of the isolation section are obtained by advancing the differential equation of the one-dimensional fluid control equation of each one-dimensional control body from the inlet of the isolation section to the outlet of the isolation section.
Further, as a preferred embodiment, (S2) the combustion chamber comprises a first expansion section and a second expansion section, the first expansion section is connected with the isolation section, the second expansion section is connected after the first expansion section, the additive process brought by the injected fuel occurs in the first expansion section of the combustion chamber, and the mixing of the fuel and the incoming flow and the combustion process occur in the second expansion section of the combustion chamber.
Further, as a preferred embodiment, (S2) for the first expansion section of the combustor, the heat release is not considered, the influence coefficients of the respective factors of the one-dimensional control bodies are expressed as mathematical expressions with respect to mach number and specific heat ratio for any one-dimensional control body of the first expansion section, the differential equation of the one-dimensional fluid control equation of the respective one-dimensional control body in the first expansion section is constructed, and the on-way flow parameter of the first expansion section is obtained by advancing the solution of the differential equation of the one-dimensional fluid control equation of the respective one-dimensional control body from the inlet of the first expansion section to the outlet of the first expansion section with the knowledge of the inlet condition and the heat release law of the first expansion section.
Further, as a preferred embodiment, (S2) for the second expansion section of the combustor, the influence coefficients of the respective factors of the one-dimensional control bodies are expressed as mathematical expressions with respect to mach number and specific heat ratio for any one of the one-dimensional control bodies of the second expansion section, regardless of the additive mass, and differential equations of the one-dimensional fluid control equations of the respective one-dimensional control bodies in the second expansion section are constructed, and the on-way flow parameters of the second expansion section are obtained by carrying out a propulsion solution on the differential equations of the one-dimensional fluid control equations of the respective one-dimensional control bodies from the inlet of the second expansion section to the outlet of the second expansion section, knowing the conditions and the law of heat release at the inlet of the second expansion section.
Further, as a preferred embodiment, (S2) further comprises calculating a mass flow rate of fuel to be added in the first expanding section of the combustor, wherein the mass flow rate of fuel to be added in the first expanding section of the combustor is calculated based on a theoretical fuel-air ratio at which fuel and air just completely react, an inflow capture flow rate and a flight equivalence ratio.
Further, as a preferred embodiment, (S2) further includes calculating the combustion efficiency of the second expansion section of the combustion chamber, wherein the combustion process takes into account the chemical equilibrium, the combustion efficiency is equal to the blending efficiency, and the combustion efficiency of the second expansion section of the combustion chamber is calculated by constructing a blending efficiency model.
Further, as a preferred embodiment, solving the overall performance parameters of the scramjet engine in (S4) comprises:
(S4.1) solving the internal thrust of the scramjet by a momentum equation;
(S4.2) solving the specific thrust of the scramjet based on the internal thrust of the scramjet, wherein the specific thrust of the scramjet is the ratio of the internal thrust of the scramjet to the mass flow of the free incoming flow captured by the air inlet channel;
(S4.3) solving the mass specific impulse of the scramjet based on the thrust in the scramjet, wherein the mass specific impulse of the scramjet is the ratio of the thrust in the scramjet to the weight flow of the consumed fuel.
The invention provides a one-dimensional performance estimation method of a scramjet based on chemical balance of a combustion chamber, which can directly and quickly calculate performance parameters such as specific thrust, specific impulse and the like of the scramjet and flow parameters at various positions along the path. The chemical equilibrium heat release process takes into account the dissociation process of the combustion products, which is consistent with actual scramjet operation. Meanwhile, compared with a zero-dimensional calculation method, the method can consider the influence of factors such as friction and additive quality on the working process of the scramjet engine. The method can make a basic judgment on the performance of the engine before further test and simulation of the engine, thereby effectively reducing the time and economic cost of the optimal design of the scramjet engine. Compared with the prior art, the invention has the advantages that:
1. the invention can comprehensively consider the influence of factors such as wall friction of the engine, fuel mass addition, chemical balance heat release, specific geometric dimension of the engine and the like on the performance of the scramjet engine. Compared with a zero-dimensional model, the estimation error is greatly reduced;
2. the maximum theoretical performance parameter of the engine can be obtained through the one-dimensional calculation process of chemical equilibrium heat release, compared with the one-dimensional calculation process of finite rate chemical reaction heat release, the method greatly shortens the time, and the total calculation time can be shortened to the second order; compared with a one-dimensional calculation process for calculating heat release based on a fuel calorific value, the chemical balance calculation method has the advantages that a chemical balance process is considered, and the working process of the actual scramjet engine is more consistent;
3. according to the invention, through one-dimensional performance pre-estimation calculation, a basic judgment can be directly and rapidly carried out on the performance parameters of the scramjet, so that the time and the economic cost of the optimal design of the scramjet can be effectively reduced. Meanwhile, the one-dimensional performance estimation method can obtain the maximum values of the working pressure and the working temperature in the combustion chamber, and can provide a basis for structural design and material selection of the combustion chamber.
The invention has been verified by test data at present, and is used for preliminary optimization work before the scramjet engine is subjected to test and simulation, and the specific verification parameter is the consistency test of the wall surface pressure distribution of the combustion chamber.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a flow chart of an embodiment of the present invention;
FIG. 2 is a schematic structural view of a scramjet engine;
FIG. 3 is a schematic diagram of a one-dimensional control body according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of an embodiment of the present invention.
Detailed Description
For the purpose of promoting a clear understanding of the objects, aspects and advantages of the embodiments of the invention, reference will now be made to the drawings and detailed description, wherein there are shown in the drawings and described below specific embodiments of the invention, in which modifications and variations can be made by one skilled in the art without departing from the spirit and scope of the invention. The exemplary embodiments of the present invention and the description thereof are provided to explain the present invention and not to limit the present invention.
The invention aims to establish a scramjet engine one-dimensional performance estimation method by considering factors such as wall surface friction, fuel addition and the like of a scramjet engine under the assumption of chemical balance heat release of a combustion chamber, and the method can directly and quickly calculate performance parameters such as specific thrust, specific impulse and the like of the scramjet engine and various physical quantities along the path. The specific operation is that flight condition parameters (such as flight altitude, flight Mach number and flight equivalence ratio) are given, the type of selected fuel and the basic geometric dimension of the scramjet are selected, physical quantities along the engine are solved through a one-dimensional calculation method, then relevant flow parameters of all sections of the scramjet shown in figure 2 are obtained, and further, overall performance parameters such as specific impulse, specific thrust and the like of the engine can be solved through a momentum theorem.
The structure schematic diagram of the scramjet engine is shown in fig. 2, and the flowing working medium in the scramjet engine conforms to an ideal gas state equation. The actual gas properties are similar to the ideal gas, and in order to simplify the calculation of the thermodynamic process, the ideal gas properties are adopted for calculation. Each thermal process of the scramjet engine does not consider heat transfer and radiation with the wall surface, namely each wall surface of the engine is regarded as an insulating wall. The flow coefficient of an air inlet of the scramjet engine is 1, and the additional flow pipe resistance, lip shock wave resistance and engine outer cover friction resistance of the air inlet are not considered. The flow combustion process in the isolation section and the supersonic combustion chamber of the scramjet engine is a quasi-one-dimensional process along the flow direction, and the influence brought by a shock wave system in the isolation section and the combustion chamber is not considered. The total enthalpy of the expansion process inside the tail pipe of the scramjet remains unchanged. The scramjet engine is in horizontal linear cruising, and the direction of inlet airflow and outlet airflow is consistent with the flying direction.
In one embodiment, referring to fig. 1, a method for estimating one-dimensional performance of a scramjet engine based on chemical equilibrium of a combustion chamber is provided, comprising the steps of:
(S1) determining flow parameters of an inlet section of an air inlet channel, and solving the flow parameters of an outlet section of the air inlet channel;
(S2) calculating the heat release amount of each axial movement step in the flow combustion process based on the chemical balance of the combustion chamber by combining the given fuel type and the flight equivalence ratio according to a differential equation of a one-dimensional fluid control equation, so as to obtain flow parameters at each position along the path of the combustion chamber according to space propulsion solution;
(S3) keeping the total enthalpy of combustion products unchanged in the expansion process of the tail nozzle, simplifying the expansion process of the tail nozzle into a variable-sectional-area friction pipeline flow process without energy addition according to given geometric parameters of the tail nozzle, constructing a fluid control differential equation in the tail nozzle, and solving flow parameters of all positions of the tail nozzle;
and (S4) solving the overall performance parameters of the scramjet.
The invention is based on the assumption of chemical balance heat release of the combustion chamber, and related performance parameters of the scramjet engine, such as specific thrust and specific impulse parameters, can be rapidly calculated, so that the overall performance of the scramjet engine can be directly preliminarily judged; in addition, the on-way flow parameters of the engine, such as temperature, pressure and the like, can be obtained through calculation, so that the pressure and the highest temperature of the internal work of the engine can be obtained, and a basis is provided for the structural design and material selection of the engine.
The step (S1) of the present invention is to solve the compression process of the scramjet engine, that is, to solve the flow parameters of the inlet cross section (cross section 0 in fig. 2) and the outlet cross section (cross section 1 in fig. 2) of the air inlet channel, and specifically includes:
(S1.1) determining a flow parameter of an inlet section of the air inlet channel;
(S1.1.1) setting the flying height of the scramjet engine
Mach number of flight
Flow rate of incoming flow
Static temperature of inlet cross section (cross section 0 in FIG. 2) of air intake duct
Static pressure ofp 0And density
；
Wherein the static temperature of the inlet cross-section of the inlet
Static pressure ofp 0And density
Can be obtained by standard atmospheric lookup table, and its specific value is only related to flying height
Related, as shown in the following formula:
(S1.1.2) simultaneously establishing a mass conservation equation, an adiabatic assumption, a sound velocity formula, a speed and Mach number relational expression and an isentropic relational expression at the inlet section of the air inlet channel, and determining flow parameters of the inlet section of the air inlet channel, including the total temperature of the inlet section of the air inlet channel
Total pressure, total pressure
Speed of the motor
And inlet cross-sectional area
。
The mass conservation equation at the inlet cross section of the inlet channel has:
the adiabatic assumption, sound velocity formula, velocity and mach number relation and isentropic relation at the inlet cross section of the air inlet channel are as follows:
in the formula (I), the compound is shown in the specification,
，
，
，
，
respectively the total enthalpy, the constant pressure specific heat, the local acoustic velocity, the specific heat ratio, the gas constant and the specific heat ratio of the gas flow at the inlet section of the air inlet passage
Can be calculated by a thermodynamic calculation program. Wherein the specific heat at constant pressure is defined by the following formula:
combining the above equations, the total temperature of the inlet cross section of the inlet
Total pressure of
Speed, velocity
And inlet cross-sectional area
It is obtained that the flow parameters to the inlet cross section of this inlet channel are determined.
(S1.2) solving the flow parameters of the outlet section of the air inlet channel;
at a known adiabatic compression efficiency
And inlet/outlet Mach number ratio of the inlet duct
Under the condition, the adiabatic assumption, the mass conservation equation and the state equation of the outlet section of the air inlet channel are combined, so that the flow parameters of the outlet section of the air inlet channel (the section 1 in fig. 2, namely the inlet section of the isolation section) can be obtained, wherein the specific equation is as follows:
in one embodiment of the invention, the air inlet channel of the scramjet engine adopts four oblique shock waves for compression, and the adiabatic compression efficiency of the air inlet channel
And may be greater than or equal to 0.9 in the mach number range studied. The 4 oblique shock wave compression modes ensure higher adiabatic compression efficiency and can meet the engineering standard of weight-structure design of the hypersonic inlet channel. Adiabatic compression efficiency set in one embodiment of the present invention
Is 0.9.
According to the adiabatic hypothesis, the intake duct inlet cross section and the intake duct outlet cross section of the scramjet engine satisfy the energy conservation equation, and have:
in the formula (I), the compound is shown in the specification,Twhich is representative of the temperature of the molten metal,
is a Mach number of the component (A),
for specific heat ratio, subscripts 0,1, t represent inlet cross-section 0, outlet cross-section 1, and the stagnation condition, respectively.
The above formula can be obtained by separating the variables:
from the above formula, when the incoming stream Mach number is large (i.e. the Mach number is large)
) Then, the above equation can be converted into:
the cycle static temperature ratio is defined here:
。
thus, as the incoming flow mach number
Continuously increasing, for a given cycle static temperature ratio
Mach number of outlet of air intake duct
Mach number of entrance
The ratio of the ratio will approach a constant. Mach number of stream
When the ratio of static temperature to circulating temperature is continuously increased
Mach number of inlet outlet at 5, 6, 7 and 8
Mach number of incoming flow
The ratios of (a) to (b) are close to 0.404, 0.425, 0.452 and 0.487 respectively. In one embodiment of the invention, the ratio of the Mach number of the inlet/outlet of the air inlet duct is set
Is 0.4.
The step (S2) of the invention is to solve the combustion process of the scramjet, namely the solution of the flow parameters from the isolation section to the combustion chamber, the flow combustion process in the isolation section of the scramjet and the supersonic combustion chamber is a quasi one-dimensional process along the flow direction, the influence brought by the shock wave system in the isolation section and the combustion chamber is not considered, and the influence brought by factors such as geometric structure, additive quality, heat release and wall surface friction can be considered.
In one embodiment, in step (S2), the step of moving is performed in axial directiondxDividing the isolation section between the inlet section of the isolation section of the scramjet engine and the outlet section of the combustion chamber and the combustion chamber into a plurality of one-dimensional control bodies, constructing a differential equation of a one-dimensional fluid control equation of each one-dimensional control body, and solving based on the differential equation of the one-dimensional fluid control equation of the constructed one-dimensional control body to obtain flow parameters at each position along the way from the isolation section to the combustion chamber.
For any one-dimensional control body, mass conservation analysis is performed on the one-dimensional control body, as shown in FIG. 3, without considering the ablative mass of the combustion chamber wall, where the mass addition comes mainly from the fuel addition
(ii) a The stress analysis is carried out on the one-dimensional control body, the resistance brought by fuel addition and the flow in the one-dimensional control body is not considered, and the stress of the one-dimensional control body is totally from wall surface friction and wall surface pressure; performing energy conservation analysis on the one-dimensional control body, and considering the wall surface as a heat insulation wall surface
Neglecting the influence of fluid on external work
The energy increment of the inlet and the outlet of the one-dimensional control body is completely from the fuel and the chemical heat release thereof. Writing the influence coefficient of each factor of the one-dimensional control body into Mach number
Specific heat ratio of
The differential equation of the one-dimensional fluid control equation of the one-dimensional control body is as follows:
in the formula (I), the compound is shown in the specification,
representing the energy carried by the fuel itself and the chemical heat release of the fuel and the incoming air, wherein the chemical heat release is calculated based on the chemical balance;
the coefficient of wall friction is generally between 0.002 and 0.005, and the value is closely related to the roughness level of the wall surface;
and
cross-sectional area, hydraulic diameter and molar mass, respectively. According to the equation set, under the condition that the inlet condition and the heat release rule are known, the on-way flow parameters of the combustion chamber can be obtained by carrying out propulsion solution according to the equation set.
Specifically, there is no mass addition and no chemical heat release within the insulation segment (i.e., between section 1 and section 2 in FIG. 2)
Therefore, the isolation section can be processed according to a friction pipeline with an equal section, only the friction resistance between the fluid and the wall surface is considered in the isolation section, for any one-dimensional control body of the isolation section, the influence coefficient of each factor of the one-dimensional control body is expressed as a mathematical expression related to the Mach number and the specific heat ratio, a differential equation of a one-dimensional fluid control equation of each one-dimensional control body in the isolation section is constructed, and under the condition that the inlet condition and the heat release rule of the isolation section are known, the on-way flow parameters of the isolation section are obtained by advancing and solving the differential equation of the one-dimensional fluid control equation of each one-dimensional control body from the inlet of the isolation section to the outlet of the isolation section.
For any one-dimensional control body in the isolation section, such as the ith one-dimensional control body in the isolation section, the differential equation of the one-dimensional fluid control equation is expressed as follows:
each parameter in the above formula is a parameter corresponding to the ith one-dimensional control body of the isolation section (i.e. the isolation section is arranged between the section 1 and the section 2 in figure 2),
the Mach number of the ith one-dimensional control body of the isolation section is the Mach number of the ith one-dimensional control body of the isolation section;
the specific heat ratio of the ith one-dimensional control body of the isolation section;
the wall surface friction coefficient of the ith one-dimensional control body of the isolation section is set;
the hydraulic diameter of the ith one-dimensional control body of the isolation section;
the total pressure of the ith one-dimensional control body of the isolation section,
the total temperature of the ith one-dimensional control body of the isolation section is controlled.
Referring to fig. 2, the combustion chamber (i.e., the combustion chamber between section 2 and section 4 in fig. 2) includes a first diverging section (i.e., the first diverging section between section 2 and section 3 in fig. 2) connected to the isolating section, and a second diverging section (i.e., the second diverging section between section 3 and section 4 in fig. 2) connected after the first diverging section. The combustion chamber relates to the mixing of fuel and incoming flow and the combustion process, and the practical process can be simplified into the mass adding process of the position of a fuel injection inlet and the heat release distribution of the fuel in the supersonic combustion chamber. In one embodiment, as shown in FIG. 2, it is assumed that the additive process from the injected fuel occurs in the first expansion section of the combustion chamber, and the mixing of the fuel with the incoming flow and the combustion process occur in the second expansion section of the combustion chamber.
In one embodiment (S2), for the first expansion section of the combustion chamber, the heat release is not taken into account
And for any one-dimensional control body of the first expansion section, expressing the influence coefficient of each factor of the one-dimensional control body as a mathematical expression related to the Mach number and the specific heat ratio, constructing a differential equation of the one-dimensional fluid control equation of each one-dimensional control body in the first expansion section, and under the condition that the inlet condition and the heat release rule of the first expansion section are known, carrying out propulsion solution on the on-way flow parameters of the first expansion section through the differential equation of the one-dimensional fluid control equation of each one-dimensional control body from the inlet of the first expansion section to the outlet of the first expansion section.
For any one-dimensional control body in the first expansion section, such as the kth one-dimensional control body in the first expansion section, the differential equation of the one-dimensional fluid control equation is as follows:
each parameter in the above equation is the first expansion section (i.e., the first expansion section between section 2 and section 3 in FIG. 2)jThe parameters corresponding to the one-dimensional control bodies,
is the first in the first expansion sectionjThe Mach number of the one-dimensional control body;
is a firstIn the expansion sectionjSpecific heat ratio of the one-dimensional control bodies;
is the first expansion sectionjThe wall friction coefficient of each one-dimensional control body;
、
、
the pressure specific heat is respectively the first in the first expansion sectionjThe cross section area, the hydraulic diameter and the molar mass of the outlet section of each one-dimensional control body;
is the first expansion sectionjThe total pressure of the one-dimensional control body,
is the first expansion sectionjThe total temperature of the one-dimensional control body,
is the first in the first expansion sectionjMass addition of the individual one-dimensional control bodies, the mass addition originating from the fuel addition.
In an embodiment (S2), the method further comprises calculating a mass flow of fuel to be added in the first expansion section of the combustor, wherein the mass flow of fuel to be added in the first expansion section of the combustor is calculated based on a theoretical fuel-air ratio at which fuel and air just completely react, an incoming flow capture flow and a flight equivalence ratio.
In particular, capturing traffic in a known incoming flow
And the equivalent ratio of flight
Under the conditions of (1), then the mass flow of fuel to be added is required
Can be obtained by the following formula:
in the formula (I), the compound is shown in the specification,
this value is the theoretical fuel-air ratio at which the fuel and air are just fully reacted, and can be determined by thermodynamic calculations.
Is the true fuel-air ratio of fuel to air.
In (S2) of an embodiment, for the second expansion section of the combustor, the additive is not considered
And for any one-dimensional control body of the second expansion section, expressing the influence coefficient of each factor of the one-dimensional control body as a mathematical expression related to the Mach number and the specific heat ratio, constructing a differential equation of the one-dimensional fluid control equation of each one-dimensional control body in the second expansion section, and under the condition that the inlet condition and the heat release rule of the second expansion section are known, carrying out propulsion solution on the on-way flow parameters of the second expansion section through the differential equation of the one-dimensional fluid control equation of each one-dimensional control body from the inlet of the second expansion section to the outlet of the second expansion section to obtain the on-way flow parameters of the second expansion section.
For any one-dimensional control body in the second expansion section, e.g. the first in the second expansion sectionkA one-dimensional control body, a differential equation of one-dimensional fluid control equation of which is as follows:
in the above formula, each parameter is the second expansion segmentkThe parameters corresponding to the one-dimensional control bodies,
is the first in the second expansion sectionkThe Mach number of the one-dimensional control body;
is the second expansion section of the second expansion sectionkSpecific heat ratio of the one-dimensional control bodies;
is the second expansion section of the second expansion sectionkThe wall friction coefficient of each one-dimensional control body;
、
、
、 
respectively in the second expansion sectionkThe cross section area, the hydraulic diameter, the molar mass and the specific heat at constant pressure of the outlet section of each one-dimensional control body;
is the first in the second expansion sectionkThe total pressure of the one-dimensional control body,
is the first in the second expansion sectionkThe total temperature of the one-dimensional control body. In the second expansion section after adding the substanceFirst, thekMolar mass of gas mixture in one-dimensional control body
Can pass throughkThe total mass and the total number of moles in the one-dimensional control body.
Represents the first in the second expansion sectionkThe energy carried by the fuel in the one-dimensional control body and the chemical heat release of the fuel and the incoming air are calculated based on chemical equilibrium.
In an embodiment (S2), the method further includes calculating a combustion efficiency of the second expansion section of the combustion chamber, the combustion process takes into account a chemical equilibrium, the combustion efficiency is equal to the blending efficiency, and the combustion efficiency of the second expansion section of the combustion chamber is calculated by constructing a blending efficiency model.
Since the combustion process takes into account the chemical equilibrium, it is assumed that the combustion efficiency is equal to the blending efficiency. Therefore, the key to solving the combustion efficiency of the second expansion section of the combustor is to give a suitable blending efficiency model.
In an embodiment of the present invention, the constructed blending efficiency model is as follows:
the axial length direction of the scramjet engine is taken as the x direction, whereinx 3The coordinate of the x-direction of the inlet section of the second expansion segment of the combustion chamber is shown,x 4showing the co-ordinate of the x-direction of the outlet cross-section of the second expansion segment of the combustion chamber,x k is the second expansion section of the combustion chamberkThe coordinate of the outlet section of the one-dimensional control body in the x direction,
indicating the fuel injection angle.
The blending efficiency model may take into account fuel injection angle
The effect on the blending efficiency is considered by the blending efficiency model, and when the injection angle is between 0 and 90 degrees, the blending efficiency can be directly interpolated by the linear interpolation of the formula, wherein the expression is as follows:
in the formula
Indicating fuel injection angle
= minimum blending efficiency at 90 degrees,
indicating fuel injection angle
Minimum blending efficiency at 0 degrees.
The method for solving the overall performance parameters of the scramjet engine in the S4 is a key means for evaluating the overall flight performance, and is commonly used for evaluating the overall performance parameters of the scramjet engine, including specific thrust and mass specific impulse. Thrust estimation of engines typically uses thrust within the engine, as there may be some variation in the flight profile for different flight conditions.
In one embodiment, step (S4) comprises:
(S4.1) solving the internal thrust of the scramjet by a momentum equation;
in the formula (I), the compound is shown in the specification,
the thrust in the scramjet engine is scramjet.
And (S4.2) solving the specific thrust of the scramjet based on the internal thrust of the scramjet, wherein the specific thrust of the scramjet is the ratio of the internal thrust of the scramjet to the mass flow of the free incoming flow captured by the air inlet channel.
Specific thrust
(unit: N · s/kg) which characterizes the thrust effect of scramjet engines. The larger the specific thrust, the larger the acceptable resistance of the scramjet engine, and thus the faster flight speed can be achieved, the expression:
and (S4.3) solving the mass specific impulse of the scramjet based on the internal thrust of the scramjet, wherein the mass specific impulse of the scramjet is the ratio of the internal thrust of the scramjet to the weight flow of the consumed fuel.
Specific mass impact
(unit: s) defines the amount of thrust that can be generated that can be characterized for a particular mass flow of fuel. The larger the mass specific impulse, the smaller the fuel mass flow required for generating the same thrust, and the longer voyage can be realized by carrying fixed mass fuel, and the expression is as follows:
in the formula (I), the compound is shown in the specification,
in order to be the acceleration of the gravity,
representing the fuel mass flow.
The invention can obtain the on-way flow parameters of the scramjet engine, namely the highest pressure and the highest temperature in the working process of each component can also be obtained, which provides effective basis for the structural design and material selection of each component of the engine.
In one embodiment, there is provided a one-dimensional performance estimation apparatus of a scramjet engine based on combustion chamber chemical balance, comprising:
the first module is used for determining the flow parameters of the inlet section of the air inlet channel and solving the flow parameters of the outlet section of the air inlet channel;
the second module is used for calculating the heat release quantity of each axial movement step in the flow combustion process based on the chemical balance of the combustion chamber by combining the given fuel type and the flight equivalence ratio according to a differential equation of a one-dimensional fluid control equation, so that the flow parameters at each position along the path of the combustion chamber are obtained through space propulsion solution;
the third module is used for keeping the total enthalpy of combustion products unchanged in the expansion process of the tail nozzle, simplifying the expansion process of the tail nozzle into a variable-sectional-area friction pipeline flow process without energy addition according to given geometric parameters of the tail nozzle, constructing a fluid control differential equation in the tail nozzle and solving flow parameters of all positions of the tail nozzle;
and the fourth module is used for solving the overall performance parameters of the scramjet engine.
The implementation method of the functions of the modules can be implemented by the same method in the foregoing embodiments, and details are not repeated here.
In this embodiment, a computer device is provided, and the computer device may be a server, and its internal structure diagram may be as shown in fig. 4. The computer device includes a processor, a memory, a network interface, and a database connected by a system bus. Wherein the processor of the computer device is configured to provide computing and control capabilities. The memory of the computer device comprises a nonvolatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program, and a database. The internal memory provides an environment for the operation of an operating system and computer programs in the non-volatile storage medium. The database of the computer device is used for storing sample data. The network interface of the computer device is used for communicating with an external terminal through a network connection. The computer program is executed by a processor to implement the steps of the method for estimating the one-dimensional performance of the scramjet based on the chemical equilibrium of the combustion chamber in the above embodiment.
Those skilled in the art will appreciate that the architecture shown in fig. 4 is merely a block diagram of some of the structures associated with the disclosed aspects and is not intended to limit the computing devices to which the disclosed aspects apply, as particular computing devices may include more or less components than those shown, or may combine certain components, or have a different arrangement of components.
In one embodiment, a computer apparatus is provided, comprising a memory storing a computer program and a processor, the processor implementing the steps of the method for estimating one-dimensional performance of a scramjet based on combustion chamber chemical equilibrium in any of the above embodiments when executing the computer program.
In one embodiment, a computer readable storage medium is provided, on which a computer program is stored, which when executed by a processor implements the steps of the method for estimating the one-dimensional performance of a scramjet based on the chemical equilibrium of the combustion chamber in any of the above embodiments.
It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above can be implemented by hardware instructions of a computer program, which can be stored in a non-volatile computer-readable storage medium, and when executed, can include the processes of the embodiments of the methods described above. Any reference to memory, storage, database or other medium used in the embodiments provided herein can include non-volatile and/or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically Programmable ROM (EPROM), electrically Erasable Programmable ROM (EEPROM), or flash memory. Volatile memory can include Random Access Memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms such as Static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double Data Rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous Link DRAM (SLDRAM), rambus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).
The technical features of the above embodiments can be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the above embodiments are not described, but should be considered as the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, and these are all within the scope of protection of the present application. Therefore, the protection scope of the present patent application shall be subject to the appended claims.
Claims (11)
1. The method for estimating the one-dimensional performance of the scramjet engine based on the chemical balance of the combustion chamber is characterized by comprising the following steps of:
(S1) determining flow parameters of an inlet section of an air inlet channel, and solving the flow parameters of an outlet section of the air inlet channel;
(S2) calculating the heat release amount of each axial motion step in the flow combustion process based on the chemical balance of the combustion chamber by combining a given fuel type and a given flight equivalence ratio according to a differential equation of a one-dimensional fluid control equation, so as to obtain flow parameters of each position along the path of the combustion chamber by space propulsion solution;
(S3) keeping the total enthalpy of combustion products unchanged in the expansion process of the tail nozzle, simplifying the expansion process of the tail nozzle into a variable-sectional-area friction pipeline flow process without energy addition according to given geometric parameters of the tail nozzle, constructing a fluid control differential equation in the tail nozzle, and solving flow parameters of all positions of the tail nozzle;
(S4) solving the overall performance parameters of the scramjet;
in (S2), in axial movement stepdxDividing an isolation section between an inlet section of the isolation section of the scramjet engine and an outlet section of a combustion chamber and the combustion chamber into a plurality of one-dimensional control bodies, constructing a differential equation of a one-dimensional fluid control equation of the one-dimensional control bodies, and solving based on the differential equation of the one-dimensional fluid control equation of the constructed one-dimensional control bodies to obtain flow parameters of each part along the way from the isolation section to the combustion chamber;
the differential equation of the one-dimensional fluid control equation for constructing the one-dimensional control body comprises the following steps:
for any one-dimensional control body, performing mass conservation analysis on the one-dimensional control body, and considering that the mass addition comes from fuel addition without considering the ablation mass of the wall surface of the combustion chamber;
the stress analysis is carried out on the one-dimensional control body, and the resistance brought by fuel addition and the flow in the one-dimensional control body is not considered, so that the stress of the one-dimensional control body is completely from wall surface friction and wall surface pressure;
performing energy conservation analysis on the one-dimensional control body, considering that the wall surface is a heat insulation wall surface and neglecting the influence of fluid on acting, so that the energy increment of the inlet and the outlet of the one-dimensional control body is completely from the fuel and the chemical heat release of the fuel and the incoming air, wherein the chemical heat release is obtained based on chemical balance calculation;
writing the influence coefficient of each factor of the one-dimensional control body into Mach number
Specific heat ratio of
The differential equation of the one-dimensional fluid control equation of the one-dimensional control body is constructed and obtained.
2. The method for estimating one-dimensional performance of the scramjet engine based on the chemical balance of the combustion chamber, according to claim 1, wherein in (S1), the flow parameters of the inlet cross section of the air inlet passage are determined, and the method comprises the following steps:
the method comprises the following steps of (1) giving the flight altitude, the flight Mach number and the inflow flow of the scramjet engine, and the static temperature, the static pressure and the density of the inlet section of an air inlet channel;
and determining flow parameters of the inlet section of the air inlet by combining a mass conservation equation, an adiabatic assumption, a sound velocity formula, a speed and Mach number relational expression and an isentropic relational expression at the inlet section of the air inlet, wherein the flow parameters comprise the total temperature, the total pressure, the speed and the inlet section area of the inlet section of the air inlet.
3. The method for estimating one-dimensional performance of scramjet engine based on chemical equilibrium of combustion chamber as claimed in claim 2, wherein in (S1), the adiabatic compression efficiency is known
Mach number ratio of inlet/outlet of inlet duct
And under the condition, determining the flow parameters of the outlet section of the air inlet channel by combining the adiabatic assumption, the mass conservation equation and the state equation at the outlet section of the air inlet channel.
4. The method for estimating one-dimensional performance of a scramjet engine based on chemical equilibrium of a combustion chamber as claimed in claim 3, wherein in (S1), adiabatic compression efficiency is set
0.9, ratio of Mach number of outlet/inlet of air inlet duct
Is 0.4.
5. The method for estimating one-dimensional performance of the scramjet engine based on the chemical balance of the combustion chamber as claimed in claim 1, wherein in (S2), the isolation section is free from mass addition and chemical heat release, the isolation section is regarded as a friction pipeline with a uniform cross section, only the friction resistance between the fluid and the wall surface is considered in the isolation section, for any one-dimensional control body of the isolation section, the influence coefficient of each factor of the one-dimensional control body is expressed as a mathematical expression about the mach number and the specific heat ratio, a differential equation of the one-dimensional fluid control equation of each one-dimensional control body in the isolation section is constructed, and under the condition that the inlet condition and the heat release rule of the isolation section are known, the on-way flow parameters of the isolation section are obtained by propelling solution through the differential equation of the one-dimensional fluid control equation of each one-dimensional control body from the inlet of the isolation section to the outlet of the isolation section.
6. The method for estimating one-dimensional performance of the scramjet engine based on the chemical balance of the combustion chamber as recited in any one of claims 1 to 5, wherein (S2) the combustion chamber comprises a first expanding section and a second expanding section, the first expanding section is connected with the isolating section, the second expanding section is connected behind the first expanding section, the additive process brought by injected fuel occurs in the first expanding section of the combustion chamber, and the mixing of the fuel and incoming flow and the combustion process occur in the second expanding section of the combustion chamber.
7. The method for estimating one-dimensional performance of a scramjet engine based on chemical balance of a combustion chamber according to claim 6, wherein in (S2), for the first extension stage of the combustion chamber, influence coefficients of various factors of the one-dimensional control bodies are expressed as mathematical expressions about Mach number and specific heat ratio for any one-dimensional control body of the first extension stage without considering heat release, differential equations of one-dimensional fluid control equations of the various one-dimensional control bodies in the first extension stage are constructed, and the on-way flow parameters of the first extension stage are obtained by advancing the differential equations of the one-dimensional fluid control equations of the various one-dimensional control bodies from the inlet of the first extension stage to the outlet of the first extension stage with knowledge of the inlet condition of the first extension stage and the mass flow rate of the fuel gas.
8. The method for estimating one-dimensional performance of a scramjet engine based on chemical balance of a combustion chamber as claimed in claim 6, wherein in (S2), for the second expansion section of the combustion chamber, the influence coefficients of the factors of the one-dimensional control bodies are expressed as mathematical expressions about Mach number and specific heat ratio for any one-dimensional control body of the second expansion section without considering additive quality, differential equations of one-dimensional fluid control equations of the one-dimensional control bodies in the second expansion section are constructed, and the on-way flow parameters of the second expansion section are obtained by advancing the differential equations of the one-dimensional fluid control equations of the one-dimensional control bodies from the inlet of the second expansion section to the outlet of the second expansion section under the condition of the inlet of the second expansion section and the law of heat release.
9. The method for estimating one-dimensional performance of a scramjet engine based on chemical balance of a combustion chamber as recited in claim 6, wherein (S2) further comprises calculating a mass flow of fuel to be added in the first extension section of the combustion chamber, wherein the mass flow of fuel to be added in the first extension section of the combustion chamber is calculated based on a theoretical fuel-air ratio, an incoming flow capture flow and a flight equivalence ratio at which fuel and air are just completely reacted.
10. The method for estimating one-dimensional performance of the scramjet engine based on the chemical balance of the combustion chamber is characterized in that (S2) the method further comprises the step of calculating the combustion efficiency of the second expansion section of the combustion chamber, the chemical balance is considered in the combustion process, the combustion efficiency is equal to the mixing efficiency, and the combustion efficiency of the second expansion section of the combustion chamber is calculated by building a mixing efficiency model.
11. The method for estimating one-dimensional performance of a scramjet based on chemical equilibrium of combustion chamber as claimed in claim 1, 2, 3, 4, 7, 8, 9 or 10, wherein the solving of the overall performance parameters of the scramjet in (S4) comprises:
solving the internal thrust of the scramjet engine by a momentum equation;
solving specific thrust of the scramjet based on the internal thrust of the scramjet, wherein the specific thrust of the scramjet is the ratio of the internal thrust of the scramjet to the mass flow of free incoming flow captured by an air inlet channel;
and solving the mass specific impulse of the scramjet based on the internal thrust of the scramjet, wherein the mass specific impulse of the scramjet is the ratio of the internal thrust of the scramjet to the weight flow of the consumed fuel.
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