CN115221638A - Performance time response analysis method for unsteady state process of sub-combustion ramjet engine - Google Patents

Performance time response analysis method for unsteady state process of sub-combustion ramjet engine Download PDF

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CN115221638A
CN115221638A CN202210961046.4A CN202210961046A CN115221638A CN 115221638 A CN115221638 A CN 115221638A CN 202210961046 A CN202210961046 A CN 202210961046A CN 115221638 A CN115221638 A CN 115221638A
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outlet
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volume
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陈玉春
刘杰
房睿远
黄新春
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Northwestern Polytechnical University
Beijing Power Machinery Institute
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Abstract

The invention relates to a performance time response analysis method of a non-steady state process of a sub-combustion ramjet, which comprises the steps of calculating the outlet flow of an air inlet channel, the total temperature and the total pressure of the sub-combustion ramjet under a steady state; establishing a simulated swash plate-volume model according to the combustion chamber of the sub-combustion ramjet engine to obtain the total temperature, the total enthalpy and the total pressure of a simulated outlet of a steady-state combustion chamber model and the outlet flow; correcting the simulated total outlet enthalpy and the outlet flow of the combustion chamber model to obtain the total outlet enthalpy and the outlet flow of the combustion chamber considering the volume effect, and combining the simulated volume to obtain an error map of the unsteady thrust change rule of the engine and the unsteady thrust change rule designed by adopting the non-design point model; the volume effect in the combustion chamber is considered in response to the performance time of the unstable state process of the engine, and the influence of the unstable state process such as acceleration and deceleration performance and large maneuvering on the performance of the impact engine can be reflected more accurately.

Description

Performance time response analysis method for unsteady state process of sub-combustion ramjet engine
Technical Field
The invention relates to the field of aircraft engines, in particular to a time response analysis method for a non-steady-state process of a ramjet engine.
Background
The ramjet engine uses oxygen in the air as an oxidant, and the carried fuel contains little or no oxidant, so that the specific impulse is obviously improved. Therefore, the missile powered by the ramjet has a longer range, lighter weight and better maneuverability, and can realize the whole-course supersonic cruise flight, thereby greatly improving the penetration resistance of the missile. Since the eighties of the last century, the research on the ram propulsion technology has been carried out in almost all countries with the missile development ability, and various ram and combined engines thereof become the preferred power devices for tactical missiles, interception missiles and cruise missiles in the present century.
In the unsteady state process, along with the change of factors such as flight attitude, flight condition, each parameter in the ramjet combustion chamber also can take place corresponding change, if can be quick learn in unsteady state process, in certain time, the response and the concrete change of each parameter can help the designer to design and appoint reasonable flight path promptly, also provides the reference for the control law who designs the ramjet. However, the performance time response of the unsteady process needs to consider the volume effect in the combustion chamber, and the performance time response characteristic is considered to reflect the acceleration and deceleration performance of the engine and the influence of the unsteady processes such as large maneuvering on the performance of the ram engine more accurately.
Disclosure of Invention
The invention aims to avoid the defects in the prior art and provides a performance time response analysis method for the unsteady state process of a scramjet, which considers the volume effect in a combustion chamber, quickly judges the unsteady state performance parameters of the ramjet, is convenient for making a reasonable flight path, shortens the iteration cycle and improves the design efficiency of the flight path.
In order to realize the purpose, the invention adopts the technical scheme that: a method for analyzing performance time response of a non-steady state process of a sub-combustion ramjet engine comprises the following steps:
step one, according to the actual flight Mach number Ma and the flight altitude H of the scramjet engine and the interpolated flow coefficient of the flight Mach number Ma on the air inlet channel interpolation characteristic diagram
Figure BDA0003792877520000023
Calculating the outlet flow, the total temperature and the total pressure of an air inlet passage under the steady state of the sub-combustion ramjet;
establishing a simulated disc-volume model according to the combustion chamber of the sub-combustion ramjet, wherein the simulated disc has no volume and is used for simulating the steady-state characteristic of the combustion chamber; the simulation volume V is the same as the actual combustion chamber volume and is used for simulating the combustion chamber volume;
based on the simulated swash plate and the inlet outlet flow, the total temperature and the total pressure of the sub-combustion ramjet in the steady state in the step one, performing pneumatic thermodynamic calculation by adopting the characteristics of the steady-state combustion chamber to obtain the total temperature T, the total enthalpy H, the total pressure P and the outlet flow W of the simulated outlet of the steady-state combustion chamber model;
step three, correcting the simulated outlet total enthalpy H and the outlet flow W of the combustion chamber model in the step (2) by adopting a formula (1) and a formula (2):
Figure BDA0003792877520000021
Figure BDA0003792877520000022
wherein V is the combustion chamber simulation volume in the step two; k is the gas specific heat ratio; r is a universal gas constant; dp/dt is the derivative of total combustor outlet pressure over time; u is the gas internal energy in the combustion chamber, the total temperature T of a simulated outlet of the steady-state combustion chamber model is obtained, and du/dt is the derivative of the gas internal energy in the combustion chamber to time;
in the formula (2), u is the internal energy of gas in the combustion chamber, and u can be represented by u, which can be the internal energy of gas in the combustion chamber before correction, or the internal energy of gas in the combustion chamber after correction, display format or implicit format.
Thus obtaining: the total enthalpy of the outlet of the combustion chamber H 'and the outlet flow W' taking the volume effect into account;
and step four, obtaining an unsteady thrust change rule of the scramjet and designing an unsteady thrust change rule error map of the scramjet by adopting an unsteady point model by utilizing the obtained total enthalpy H 'and the outlet flow W' of the combustion chamber considering the volume effect and the simulated volume V and selecting a time step, and obtaining the characteristic variable of the performance time response of the scramjet.
Further, the third step specifically includes the following steps:
step 31, differentiating the total pressure P of the simulated outlet of the steady-state combustion chamber model in the step two by using an implicit Euler format, and then obtaining the total temperature T of the simulated outlet of the steady-state combustion chamber model according to the total pressure P and the total enthalpy H of the simulated outlet of the steady-state combustion chamber model;
the flow rate W' after taking the volume effect into consideration is calculated by the formula (1),
Figure BDA0003792877520000031
in the formula, dp/dt is the derivative of total pressure at the outlet of the combustion chamber with respect to time; dp is the differential of the total pressure; v is the simulation volume, namely the actual combustion chamber volume; t and W are the simulated total outlet temperature and outlet flow of the steady-state combustion chamber model in the step two; r is a universal gas constant;
step 32, obtaining a formula (4) according to an internal energy conversion formula by testing the total outlet temperature T':
U'＝H-T'·R (4)
in the formula, U' is the gas internal energy in the combustion chamber after considering the volume effect; h is the total enthalpy of the simulated outlet of the steady-state combustion chamber model, and R is a universal gas constant;
and 33, carrying out differential processing on the formula (4), and converting according to a gas internal energy differential formula in the combustion chamber to obtain a calculation formula (5) of the total enthalpy H' considering the volume effect:
Figure BDA0003792877520000032
in the formula, dU' is the differential of the internal energy of the gas in the combustion chamber after considering the volume effect; dU'/dt is the derivative of the internal energy of the gas in the combustion chamber over time after taking into account the volume effect; total pressure and outlet flow of simulation outlets of the P and W steady-state combustion chamber models; v is the simulation volume, namely the actual combustion chamber volume; r is a universal gas constant;
step 34, calculating the total temperature T 'of the outlet of the combustion chamber considering the volume effect through a simple iteration method until the total temperature T' of the test outlet is utilized, and calculating to obtain the total enthalpy H 'considering the volume effect and the actual total enthalpy H' of the total temperature T 'of the test outlet according to the relation between the actual total enthalpy and the total temperature of the outlet of the combustion chamber in the iteration process according to the formula (4) and the formula (5)' Fruit of Chinese wolfberry Equal; otherwise, continuously iterating to try to obtain the total outlet temperature T ', and finally iterating to obtain the total temperature T', the total enthalpy H 'and the flow W' of the outlet of the combustion chamber after considering the volume effect.
Further, in the third step, solving the formula (1) and the formula (2) adopts a method of differentiating all differential terms by adopting an implicit euler format to obtain a formula (3):
Figure BDA0003792877520000041
in the formula, y i Is the current time value; y is i-1 Is the time value of the last moment in time, at each time stepIn the calculation, only the value of the last time is known, but the current value is unknown, so that Newton-Leptosen iterative solution is adopted for the formula (1) and the formula (2); specific values for W 'and H' were obtained.
The invention has the beneficial effects that: the method considers the volume effect in the combustion chamber in response to the performance time of the unsteady process of the engine, can more accurately reflect the acceleration and deceleration performance of the engine and the influence of the unsteady processes such as large maneuvering and the like on the performance of the impact engine on the performance time response characteristic of the engine, helps design and testing personnel to quickly judge whether the unsteady performance parameters meet the requirements, makes a reasonable flight path, shortens the iteration period and improves the design efficiency.
Drawings
FIG. 1 is a schematic diagram of a "swash plate-volume" model;
FIG. 2 is a graphical representation of a calculation of engine combustion chamber volume effects;
FIG. 3 is a schematic flow chart of the volume effect calculation;
FIG. 4 is a design result of the performance time response characteristic of the non-steady state process.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
In order to achieve the above object, the present invention provides the following embodiments:
example 1: as shown in fig. 1-4, a method for analyzing the performance time response characteristics of the unsteady state process of the sub-combustion ramjet engine comprises the following steps:
(1) According to the actual flight Mach number Ma and the flight altitude H of the scramjet engine and the interpolated flow coefficient of the flight Mach number Ma on the air inlet channel interpolation characteristic diagram
Figure BDA0003792877520000051
Calculating the outlet flow of the air inlet channel, the total temperature and the total pressure of the scramjet in a steady state;
(2) As shown in fig. 1, establishing a simulated swash plate-volume model according to a combustion chamber of the sub-combustion ramjet engine, wherein the simulated swash plate has no volume and is used for simulating the steady-state characteristic of the combustion chamber; the simulation volume V is the same as the actual combustion chamber volume and is used for simulating the combustion chamber volume;
based on the simulated swash plate and the outlet flow, the total temperature and the total pressure of the air inlet passage in the stable state of the sub-combustion ramjet in the step (1), performing pneumatic thermal calculation by adopting the characteristics of the stable combustion chamber to obtain the total temperature T, the total enthalpy H, the total pressure P and the outlet flow W of the simulated outlet of the stable combustion chamber model;
(3) As shown in fig. 2 and fig. 3, differentiating the total pressure P of the simulated outlet of the steady-state combustor model in step (2) by using an implicit euler format, and then obtaining the total temperature T of the simulated outlet of the steady-state combustor model according to the total pressure P and the total enthalpy H of the simulated outlet of the steady-state combustor model;
the flow rate W' after taking the volume effect into consideration is calculated from formula (1),
Figure BDA0003792877520000061
in the formula, dp/dt is the derivative of total pressure at the outlet of the combustion chamber with respect to time; dp is the differential of the total pressure; v is the simulation volume, namely the actual combustion chamber volume; t and W are the simulated total outlet temperature and outlet flow of the steady-state combustion chamber model in the step (2); r is a universal gas constant;
(4) And (3) obtaining a total temperature T' of the test taking-out port according to an internal energy conversion formula to obtain a formula (4):
U'＝H-T'·R (4)
in the formula, U' is the gas internal energy in the combustion chamber after considering the volume effect; h is the total enthalpy of the simulated outlet of the steady-state combustion chamber model, and R is a universal gas constant;
(5) And (3) carrying out differential processing on the formula (4), and converting according to an internal energy differential formula to obtain a calculation formula (5) of the total enthalpy H' considering the volume effect:
Figure BDA0003792877520000062
in the formula, dU' is the differential of the internal energy of the gas in the combustion chamber after considering the volume effect; dU'/dt is the derivative of the internal energy with respect to time after accounting for the volume effect; total pressure and outlet flow of a simulated outlet of the P and W steady-state combustion chamber models; v is the simulation volume, namely the actual combustion chamber volume; r is a universal gas constant;
the implicit format of U 'in the formula (5) is the corrected gas internal energy in the combustion chamber, so the formula (5) is represented by U'.
(6) Calculating the total temperature T 'of the outlet of the combustion chamber considering the volume effect by a simple iteration method until the total temperature T' of the outlet of the test extraction port is utilized, and calculating to obtain the total enthalpy H 'considering the volume effect and the actual total enthalpy H' obtained by calculating the total temperature T 'of the outlet of the test extraction port according to the relationship between the actual total enthalpy and the total temperature of the outlet of the combustion chamber in the iteration process according to the formula (4) and the formula (5)' Fruit of Chinese wolfberry Equal; otherwise, continuously iterating to try to obtain the total outlet temperature T ', and finally iterating to obtain the total temperature T', the total enthalpy H 'and the flow W' of the outlet of the combustion chamber after considering the volume effect.
Solving the formula (1) and the formula (2), and performing difference on all differential terms by adopting an implicit Euler format to obtain a formula (3):
Figure BDA0003792877520000071
in the formula, y i Is the current time value; y is i-1 The time value of the previous moment is obtained, and when the time value is calculated on each time step, only the value of the previous moment is known, but the current value is unknown, so that Newton-Lepton iterative solution is adopted for the formula (1) and the formula (2); specific values for W 'and H' were obtained.
(7) And obtaining an unsteady thrust change rule error diagram of the scramjet and an unsteady thrust change rule error diagram of the scramjet designed by adopting a non-design point model by utilizing the obtained total enthalpy H 'and the outlet flow W' of the combustion chamber considering the volume effect and the simulated volume V and selecting the time step length, so as to obtain the characteristic variable of the performance time response of the scramjet.
The specific calculation example is as follows:
the input design points of the unsteady state process of the ramjet according to the embodiment include: the flight Mach number Ma =3.5, the flight height H =20000m, the inlet flow Wa =10.0kg/s, the total pressure recovery coefficient sigma =0.524, and the flow coefficient
Figure BDA0003792877520000072
Total pressure recovery coefficient sigma of transition section design point 2des =0.9, total pressure recovery coefficient σ of the combustion chamber in cold state 3des =0.93, combustion efficiency η b =0.92, combustor inlet Mach number Ma 3 =0.1, total outlet temperature T 4 =2000K, determining the outlet back pressure P of the exhaust nozzle as a function of the flight altitude s0 ＝4325.2Pa。
Oil supply amount W in the unsteady state process of the ramjet engine of the embodiment fb Time variation law over Time: the amount of oil supplied was increased linearly from 0.2kg/s to 0.4kg/s within 4 s. The time step calculated is 0.05s.
As shown in FIG. 4, the non-steady-state performance of the engine is designed by adopting a non-design point model, and the change rule of the thrust is shown in FIG. 4Case 1. Given a combustion chamber volume V =1m3, the variation law of the thrust is shown in fig. 4case 2. The relative error between the two is shown by the blue line in fig. 4. After the volume effect is considered, the performance time response characteristic of the unsteady state process lags behind 0.4s, and the thrust is relatively lost by 1%, namely the time of the unsteady state performance time response of the scramjet engine and the change of the thrust are quickly obtained, the estimation of the unsteady state performance of the engine is convenient, the volume effect model is adopted, the influence of the volume of a combustion chamber can be considered during the calculation of the unsteady state performance of the engine, and the estimation result is more accurate.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.

Claims (3)

1. A method for analyzing performance time response of a non-steady state process of a sub-combustion ramjet engine is characterized by comprising the following steps:
step one, according to the actual flight Mach number Ma and the flight altitude H of the scramjet engine and the interpolated flow coefficient of the flight Mach number Ma on the air inlet channel interpolation characteristic diagram
Figure FDA0003792877510000013
Calculating the outlet flow of the air inlet channel, the total temperature and the total pressure of the scramjet in a steady state;
establishing a simulated disc-volume model according to the combustion chamber of the sub-combustion ramjet, wherein the simulated disc has no volume and is used for simulating the steady-state characteristic of the combustion chamber; the simulation volume V is the same as the actual combustion chamber volume and is used for simulating the combustion chamber volume;
based on the simulated swash plate and the inlet outlet flow, the total temperature and the total pressure of the sub-combustion ramjet in the steady state in the step one, performing pneumatic thermodynamic calculation by adopting the characteristics of a steady-state combustion chamber to obtain the total temperature T, the total enthalpy H, the total pressure P and the outlet flow W of the simulated outlet of the steady-state combustion chamber model;
step three, correcting the simulated outlet total enthalpy H and the outlet flow W of the combustion chamber model in the step (2) by adopting a formula (1) and a formula (2):
Figure FDA0003792877510000011
Figure FDA0003792877510000012
wherein V is the combustion chamber simulation volume in the step two; k is the gas specific heat ratio; r is a universal gas constant; dp/dt is the time derivative of the total pressure at the outlet of the combustion chamber; u is the gas internal energy in the combustion chamber, the total temperature T of a simulation outlet of the steady-state combustion chamber model is obtained, and du/dt is the derivative of the gas internal energy in the combustion chamber to time;
thus obtaining: the total enthalpy H 'and the outlet flow W' of the outlet of the combustion chamber considering the volume effect;
and step four, obtaining an unsteady thrust change rule error diagram of the scramjet and designing the unsteady thrust change rule error diagram of the scramjet by adopting an un-designed point model by utilizing the obtained total enthalpy H 'and the outlet flow W' of the combustion chamber considering the volume effect and the simulated volume V and selecting a time step, and obtaining the characteristic variable of the performance time response of the scramjet.
2. The method for analyzing the performance time response of the non-steady state process of the sub-combustion ramjet engine as recited in claim 1, wherein said step three specifically comprises the steps of:
step 31, differentiating the total pressure P of the simulated outlet of the steady-state combustion chamber model in the step two by using an implicit Euler format, and then obtaining the total temperature T of the simulated outlet of the steady-state combustion chamber model according to the total pressure P and the total enthalpy H of the simulated outlet of the steady-state combustion chamber model;
the flow rate W' after taking the volume effect into consideration is calculated from formula (1),
Figure FDA0003792877510000021
in the formula, dp/dt is the derivative of total pressure at the outlet of the combustion chamber with respect to time; dp is the differential of the total pressure; v is the simulation volume, namely the actual combustion chamber volume; t and W are the simulated total outlet temperature and outlet flow of the steady-state combustion chamber model in the step two; r is a universal gas constant;
step 32, obtaining a formula (4) according to an internal energy conversion formula by testing the total outlet temperature T':
U'＝H-T'·R (4)
in the formula, U' is the gas internal energy in the combustion chamber after considering the volume effect; h is the total enthalpy of the simulated outlet of the steady-state combustion chamber model, and R is a universal gas constant;
and 33, carrying out differential processing on the formula (4), and converting according to a gas internal energy differential formula in the combustion chamber to obtain a calculation formula (5) of the total enthalpy H' considering the volume effect:
Figure FDA0003792877510000022
in the formula, dU' is the differential of the internal energy of the gas in the combustion chamber after considering the volume effect; dU'/dt is the derivative of the internal energy of the gas in the combustion chamber over time after taking into account the volume effect; total pressure and outlet flow of a simulated outlet of the P and W steady-state combustion chamber models; v is the simulation volume, namely the actual combustion chamber volume; r is a universal gas constant;
and step 34, calculating the total temperature T 'of the outlet of the combustion chamber considering the volume effect by a simple iteration method until the total temperature T' of the trial taking-out port is utilized, and calculating to obtain the total enthalpy H 'considering the volume effect and the actual total enthalpy H' of the total temperature T 'of the trial taking-out port according to the relation between the actual total enthalpy and the total temperature of the outlet of the combustion chamber in the iteration process according to the formula (4) and the formula (5)' Fruit of Chinese wolfberry Equal; otherwise, continuously iterating to try to obtain the total temperature T 'of the outlet, and finally iterating to obtain the total temperature T', the total enthalpy H 'and the flow W' of the outlet of the combustion chamber after considering the volume effect.
3. The method for analyzing the performance time response of the unsteady state process of the sub-combustion ramjet engine as claimed in claim 1 or 2, wherein the solving of the formula (1) and the formula (2) in the third step is carried out by differentiating all differential terms in an implicit Euler format to obtain the formula (3):
Figure FDA0003792877510000031
in the formula, y i Is the current time value; y is i-1 Is the time value of the last time instant,when calculating on each time step, only the value of the last time is known, but the current value is unknown, so that Newton-Leptosen iterative solution is adopted for the formula (1) and the formula (2); specific values for W 'and H' were obtained.
CN202210961046.4A 2022-08-11 2022-08-11 Performance time response analysis method for unsteady state process of sub-combustion ramjet engine Pending CN115221638A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117740384A (en) * 2024-02-07 2024-03-22 中国航发四川燃气涡轮研究院 Combustion performance sensitivity assessment method and device

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117740384A (en) * 2024-02-07 2024-03-22 中国航发四川燃气涡轮研究院 Combustion performance sensitivity assessment method and device
CN117740384B (en) * 2024-02-07 2024-04-16 中国航发四川燃气涡轮研究院 Combustion performance sensitivity assessment method and device

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