CN112668201A - Supersonic combustion chamber fuel injection design method based on non-uniform air flow of air inlet - Google Patents
Supersonic combustion chamber fuel injection design method based on non-uniform air flow of air inlet Download PDFInfo
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Abstract
The application relates to a supersonic combustion chamber fuel injection design method based on non-uniform air flow of an air inlet, which comprises the following steps: and obtaining the spray hole parameters of the combustion chamber according to the supersonic speed air inlet channel parameters and the engine parameters, wherein the spray hole parameters comprise the spray hole quantity, the spray hole grouping and the spray hole aperture range. The setting distance range of the injection holes is obtained according to the fuel diffusion characteristic and the ignition delay characteristic. And obtaining the setting angle range of the spray holes according to the distribution angle of the low-speed airflow region in the combustion chamber, and obtaining the global equivalence ratio of each group of spray holes according to the angle proportion of the distribution angle in the airflow flow direction section. The method determines the arrangement mode of the spray holes based on the circumferential distribution characteristics of the airflow velocity of the fuel on the flow direction section of the combustion chamber, can improve the mixing combustion efficiency of the fuel in the circumferential direction and the radial direction of the circular section of the combustion chamber, and further improves the thrust performance of the engine.
Description
Technical Field
The application relates to the field of supersonic combustor configuration design, in particular to a supersonic combustor fuel injection design method based on non-uniform air flow of an air inlet.
Background
The air flow speed in the combustion chamber of the scramjet engine is high, the residence time of fuel is short, and the robust and efficient combustion is very difficult to organize, so that the efficient mixing combustion of the fuel and incoming flow needs to be realized by adopting a proper fuel injection scheme. The fuel injection scheme is usually combined with a flame stabilization scheme in a combustion chamber, and is generally divided into two categories, one category is a support plate injection scheme in the combustion chamber, a support plate is arranged in a flow channel of the combustion chamber, and fuel is injected through an injection hole on the support plate and is directly mixed with incoming air to be combusted in the flow channel; the other type is a lateral jet injection scheme on the wall surface, and high-pressure fuel enters a combustion chamber from an injection hole by installing a fuel nozzle on the wall surface of the combustion chamber to form a lateral jet and combust in a flame stabilizer (such as a concave cavity).
The transverse jet injection scheme on the wall surface injects fuel on the wall surface, has simple structure and small aerodynamic resistance, can form a relatively high-efficiency fuel injection mixing and flame stabilizing integrated scheme of the scramjet combustor by combining a concave cavity flame stabilizer, and has the technical difficulty of improving the penetration depth of fuel and realizing the maximum uniform mixing of the fuel and incoming air. Therefore, the fuel injection scheme and the combustion chamber profile need to be designed reasonably to ensure that the performance of the combustion chamber meets the requirements in a certain working range of the engine. The current commonly used wall surface injection scheme is that a plurality of rows of spray holes are uniformly distributed in the circumferential direction, included angles are formed among the spray holes, the interaction of injection plumes is enhanced, and the scheme is used for realizing the uniform distribution of fuel in the circumferential direction by enlarging the contact area of air and fuel. However, due to jet dispersion, the penetration depth of a single jet is limited by the jet area and the jet pressure.
Disclosure of Invention
In view of the above, there is a need to provide a supersonic combustor fuel injection design method based on inlet non-uniform airflow, which can improve the supersonic combustor fuel injection depth.
A supersonic combustion chamber fuel injection design method based on non-uniform air flow of an air inlet comprises the following steps:
and obtaining the spray hole parameter values of the spray holes in the combustion chamber according to preset supersonic speed air inlet channel parameters and engine parameters. The spray hole parameters comprise spray hole number, spray hole grouping data and spray hole aperture range values.
And obtaining a set distance range value of the jet hole according to preset fuel oil diffusion characteristic data and fuel oil ignition delay characteristic data.
The distribution angle of the low-speed airflow zone is obtained according to the airflow flow velocity circumferential characteristics of the airflow flowing to the cross section of the combustion chamber, the set angle range value of the spray holes is obtained according to the distribution angle, and the global equivalent ratio of each group of spray holes is obtained according to the angle proportion value of the distribution angle in the airflow flowing to the cross section.
And obtaining fuel injection design data of the supersonic combustion chamber according to the jet hole parameter values, the set distance range values and the set angle range values of the jet holes and the global equivalent ratio of each group of jet holes.
In one embodiment, the step of obtaining the nozzle hole parameter value of the nozzle hole in the combustion chamber according to the preset supersonic air inlet channel parameter and the combustion chamber parameter comprises the following steps:
the method comprises the steps of obtaining preset supersonic speed air inlet channel parameters, engine working equivalence ratio parameters, engine stamping starting characteristic parameters and engine structure constraint parameters, and obtaining total fuel flow, number of spray holes and spray hole grouping data of the spray holes in a combustion chamber according to the obtained parameters.
And obtaining the corresponding upper limit value of the fuel injection pressure, the average flow value of the single jet orifice and the upper limit flow value of the single jet orifice according to the structural constraint parameters of the engine, and calculating the range value of the jet orifice aperture according to the obtained values.
In one embodiment, the jet hole injects gaseous fuel;
the calculation mode of the range value of the aperture of the spray hole comprises the following steps:
wherein j1 is the aperture range value of the spray orifice, mjIs the injection flow value of a single spray hole, gamma is the specific heat ratio of fuel, PjAt a gas injection pressure value, pjAnd the fuel density value is obtained.
In one embodiment, the jet hole injects liquid fuel;
the calculation mode of the range value of the aperture of the spray hole comprises the following steps:
wherein j1 is the aperture range value of the spray orifice, v is the kinematic viscosity of the fuel oil, K is the pipe diameter coefficient, mjInjection flow value, p, for a single orificejIs the fuel density value, DeltaPjThe injection pressure drop value is liquid.
In one embodiment, the obtaining of the setting angle range value of the nozzle hole according to the distribution angle includes:
and uniformly arranging the first group of spray holes on the wall surface of the combustion chamber corresponding to the distribution angle to obtain the range value of the arrangement angle of the first group of spray holes.
And uniformly arranging the rest spray holes on the wall surface of the combustion chamber outside the corresponding range of the distribution angle to obtain the range value of the arrangement angle of the spray holes and the grouped spray holes.
In one embodiment, the injection hole parameter values further comprise a first component value of an included angle between an injection direction and a wall surface of the combustion chamber in the airflow direction, and a second component value of an included angle between the injection direction and a normal direction of the injection hole wall surface in the airflow direction section of the combustion chamber. The first component value and the second component value both range from 45 degrees to 135 degrees.
In one embodiment, when the preset engine working range is Ma 2-4, the value range of the first component value is 45-115 degrees. When the preset engine working range is larger than Ma4, the value range of the first component value is 60-135 degrees.
A supersonic combustor fuel injection design device based on inlet non-uniform airflow comprises:
and the spray hole parameter calculation module is used for obtaining spray hole parameter values of spray holes in the combustion chamber according to preset supersonic speed air inlet channel parameters and engine parameters. The spray hole parameters comprise spray hole number, spray hole grouping data and spray hole aperture range values.
And the jet hole setting distance calculation module is used for obtaining the setting distance range value of the jet hole according to the preset fuel oil diffusion characteristic data and the preset fuel oil ignition delay characteristic data.
The nozzle setting angle and equivalent ratio calculation module is used for obtaining the distribution angle of the low-speed airflow region according to the airflow flow velocity circumferential characteristics of the airflow flowing to the section of the combustion chamber, obtaining the setting angle range value of the nozzle according to the distribution angle, and obtaining the global equivalent ratio of each group of nozzles according to the angle ratio of the distribution angle in the airflow flowing section.
And the fuel injection design module is used for obtaining fuel injection design data of the supersonic combustion chamber according to the jet hole parameter values, the set distance range values and the set angle range values of the jet holes and the global equivalent ratio of each group of jet holes.
A computer device comprising a memory and a processor, the memory storing a computer program, the processor implementing the following steps when executing the computer program:
and obtaining the spray hole parameter values of the spray holes in the combustion chamber according to preset supersonic speed air inlet channel parameters and engine parameters. The spray hole parameters comprise spray hole number, spray hole grouping data and spray hole aperture range values.
And obtaining a set distance range value of the jet hole according to preset fuel oil diffusion characteristic data and fuel oil ignition delay characteristic data.
The distribution angle of the low-speed airflow zone is obtained according to the airflow flow velocity circumferential characteristics of the airflow flowing to the cross section of the combustion chamber, the set angle range value of the spray holes is obtained according to the distribution angle, and the global equivalent ratio of each group of spray holes is obtained according to the angle proportion value of the distribution angle in the airflow flowing to the cross section.
And obtaining fuel injection design data of the supersonic combustion chamber according to the jet hole parameter values, the set distance range values and the set angle range values of the jet holes and the global equivalent ratio of each group of jet holes.
A computer-readable storage medium, on which a computer program is stored which, when executed by a processor, carries out the steps of:
and obtaining the spray hole parameter values of the spray holes in the combustion chamber according to preset supersonic speed air inlet channel parameters and engine parameters. The spray hole parameters comprise spray hole number, spray hole grouping data and spray hole aperture range values.
And obtaining a set distance range value of the jet hole according to preset fuel oil diffusion characteristic data and fuel oil ignition delay characteristic data.
The distribution angle of the low-speed airflow zone is obtained according to the airflow flow velocity circumferential characteristics of the airflow flowing to the cross section of the combustion chamber, the set angle range value of the spray holes is obtained according to the distribution angle, and the global equivalent ratio of each group of spray holes is obtained according to the angle proportion value of the distribution angle in the airflow flowing to the cross section.
And obtaining fuel injection design data of the supersonic combustion chamber according to the jet hole parameter values, the set distance range values and the set angle range values of the jet holes and the global equivalent ratio of each group of jet holes.
Compared with the prior art, the supersonic combustion chamber fuel injection design method, the supersonic combustion chamber fuel injection device, the computer equipment and the storage medium based on the non-uniform air flow of the air inlet channel obtain the number, the grouping, the aperture range and the setting distance range of the spray holes in the combustion chamber according to the supersonic air inlet channel parameters and the engine parameters of the engine, the diffusion characteristics and the ignition delay characteristics of the fuel. And obtaining the set angle range and the global equivalent ratio of the spray holes according to the distribution angle and the distribution ratio of the airflow flowing to the low-speed airflow region on the cross section of the combustion chamber, thereby obtaining the fuel injection design result of the supersonic combustion chamber. The setting mode of the spray holes is determined based on the circumferential distribution characteristics of the air flow velocity of the fuel on the flow direction cross section of the combustion chamber, the circumferential and radial mixed combustion efficiency of the fuel on the circular cross section of the combustion chamber can be improved, and the thrust performance of the engine is further improved.
Drawings
FIG. 1 is a diagram of an application scenario of a supersonic combustor fuel injection design method based on inlet non-uniform airflow in one embodiment;
FIG. 2 is a diagram illustrating steps in a method for designing fuel injection in a supersonic combustor based on port non-uniform airflow according to one embodiment;
FIG. 3 is a schematic illustration of the location of a wide near-wall low velocity region within the combustion chamber in one embodiment;
FIG. 4 is a schematic view of an exemplary nozzle setting angle parameter;
FIG. 5 is a schematic view of a nozzle setting angle parameter according to another embodiment;
FIG. 6 is a diagram illustrating an internal structure of a computer device according to an embodiment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
The supersonic combustion chamber fuel injection design method based on the non-uniform air flow of the air inlet can be applied to the application environment shown in FIG. 1. Fig. 1 shows a sidewall of a supersonic combustor side section, where 101 is a supersonic inlet, 102 is a supersonic combustor injection section, 103 is a cavity flame stabilizer, 104 is an engine tail nozzle, 105 is an engine profile central axis, and 106 is combustor incoming air and its flow direction.
In one embodiment, as shown in fig. 2, a fuel injection design method for a supersonic combustion chamber based on port non-uniform airflow is provided, which is described by taking the design of a fuel injection scheme applied to the engine in fig. 1 as an example, and comprises the following steps:
step 202, obtaining a spray hole parameter value of a spray hole in the combustion chamber according to preset supersonic air inlet channel parameters and engine parameters. The spray hole parameters comprise spray hole number, spray hole grouping data and spray hole aperture range values.
Specifically, for a given supersonic port parameter, the total engine combustion chamber fuel flow, the nozzle grouping, and the nozzle number are determined based on the requirements for the ram start characteristics, structural constraints, and the engine operating equivalence ratio. The general fuel spray holes are divided into 2-4 groups, and 4 groups of spray holes are adopted in the embodiment and are represented as Q1, Q2, Q3 and Q4; each group having about 4 to 8 orifices, the number of orifices in each group being represented by NQ1, NQ2, NQ3, and NQ 4. And determining the aperture range of the jet hole according to the upper limit of the fuel injection pressure and the average flow and the upper limit flow of the single jet hole in the structural constraint of the engine.
And step 204, obtaining a set distance range value of the jet hole according to preset fuel diffusion characteristic data and fuel ignition delay characteristic data.
The setting distance range of the jet holes is determined based on the diffusion characteristic and ignition delay characteristic of the engine fuel and the structural parameter constraint of the engine, and is represented by the distance range of the jet hole setting position and the front edge of the concave cavity in the embodiment.
And step 206, obtaining the distribution angle of the low-speed airflow region according to the airflow flow velocity circumferential characteristic of the airflow flow direction section of the combustion chamber, obtaining the set angle range value of the spray holes according to the distribution angle, and obtaining the global equivalent ratio of each group of spray holes according to the angle proportion of the distribution angle in the airflow flow direction section.
Specifically, in a real scramjet engine, high-speed airflow is subjected to the compression action of the wall surface of an air inlet when passing through the air inlet, and the circumferential airflow parameter distribution has strong non-uniform characteristics after entering a combustion chamber. The asymmetric nature of the combustor inlet flow does not disappear as the flow moves downstream, but rather affects the penetration depth of the individual fuel jets within the combustor. Based on the characteristic, the embodiment arranges the fuel spray holes on the wall surface of the combustion chamber corresponding to the low-speed airflow area, and correspondingly arranges the equivalent proportion of the fuel spray holes in the low-speed airflow area according to the angle proportion of the low-speed airflow area, thereby considering the influence of circumferential non-uniformity of airflow in the combustion chamber of the engine after passing through the air inlet on the injection penetration depth and enhancing the radial mixing effect of the fuel by using the low-speed airflow area.
And 208, obtaining fuel injection design data of the supersonic combustion chamber according to the jet hole parameter values, the set distance range values and the set angle range values of the jet holes and the global equivalent ratio of each group of jet holes.
The method provided by the embodiment determines the arrangement mode of the spray holes based on the circumferential distribution characteristics of the airflow velocity of the fuel on the flow direction section of the combustion chamber, can improve the mixing combustion efficiency of the fuel in the circumferential direction and the radial direction of the circular section of the combustion chamber, and further improves the thrust performance of the engine.
In one embodiment, a supersonic combustion chamber fuel injection design method based on inlet non-uniform airflow is provided, and comprises the following steps:
and 302, acquiring preset supersonic speed air inlet channel parameters, engine working equivalence ratio parameters, engine stamping starting characteristic parameters and engine structure constraint parameters, and acquiring total fuel flow, number of spray holes and spray hole grouping data of the spray holes in the combustion chamber according to the acquired parameters.
And 304, obtaining a corresponding fuel injection pressure upper limit value, a single jet orifice average flow value and a single jet orifice upper limit flow value according to the structural constraint parameters of the engine, and calculating a jet orifice aperture range value according to the obtained values.
The calculation method of the aperture range value of the spray hole when the spray hole sprays the gaseous fuel comprises the following steps:
wherein j1 is the aperture range value of the spray orifice, mjIs the injection flow value of a single spray hole, gamma is the specific heat ratio of fuel, PjAt a gas injection pressure value, pjAnd the fuel density value is obtained.
The calculation method of the aperture range value of the spray hole when the spray hole sprays the liquid fuel comprises the following steps:
wherein j1 is the aperture range value of the spray orifice, v is the kinematic viscosity of the fuel oil, K is the pipe diameter coefficient, mjInjection flow value, p, for a single orificejIs the fuel density value, DeltaPjThe injection pressure drop value is liquid.
And step 306, obtaining a distribution angle of the low-speed airflow region according to the airflow flow velocity circumferential characteristic of the airflow flow direction section of the combustion chamber, and obtaining a set angle range value of the jet holes according to the distribution angle. And uniformly arranging the first group of spray holes on the wall surface of the combustion chamber corresponding to the distribution angle to obtain the range value of the arrangement angle of the first group of spray holes. And uniformly arranging the rest spray holes on the wall surface of the combustion chamber outside the corresponding range of the distribution angle to obtain the range value of the arrangement angle of the spray holes and the grouped spray holes.
Specifically, the characteristics of the circumferential non-uniformity of the flow direction section in the supersonic combustion chamber of the front air inlet passage are shown in fig. 3. Wherein, the shadow represents a large-range near-wall low-speed area close to the wall surface of the gas chamber, the corresponding distribution angle is a4, and the distribution angle of another large-range near-wall low-speed area is a 5. It is noted that different port configurations may cause variations in the non-uniformity characteristics of the combustion chamber, and thus the number and magnitude of the distribution angles may vary from port to port.
The first group of spray holes Q1 are distributed within the range of the distribution angles a4 and a5 of the near-wall low-speed area, and the single spray holes are spaced at an angle
The second group to the fourth group of spray holes are uniformly distributed on the wall surface of the combustion chamber corresponding to the non-low-speed area, and the interval angles among the spray holes are as follows:
when the angle range of the spray holes and the interval angle of the single spray holes are determined, the angle a2 between the connection line of the spray hole position and the cross section center of the combustion chamber and the vertical axial direction can be obtained, as shown in FIG. 4. In fig. 4, a3 is the component of the normal angle between the injection hole fuel injection direction and the injection hole wall surface in the cross section, 402 is the wall surface cross section which passes through the center of a group of injection holes and is perpendicular to the flow direction, and 401 is the vertical axis of the cross section.
And 308, obtaining the global equivalent ratio of each group of spray holes according to the angle proportion of the distribution angle in the airflow flow direction section.
In this embodiment, the global equivalence ratio of the first group of nozzles is calculated in the following manner:
And 208, obtaining fuel injection design data of the supersonic combustion chamber according to the jet hole parameter values, the set distance range values and the set angle range values of the jet holes and the global equivalent ratio of each group of jet holes.
Furthermore, the obtained fuel injection design data can be optimized by combining numerical simulation and tests, and the fuel injection angle, the distance of each group of spray holes, the circumferential layout of the spray holes, the spray hole aperture and the injection pressure distribution are adjusted to obtain the best mixing effect. And (4) utilizing the optimization result to give an optimal configuration scheme of the combustion chamber in a given engine working range.
The embodiment provides a specific jet hole parameter and jet hole position design method, and a fuel injection design scheme for enhancing mixing efficiency can be obtained according to engine parameters.
In one embodiment, the injection hole parameter values further comprise a first component value of an included angle between an injection direction and a wall surface of the combustion chamber in the airflow direction, and a second component value of an included angle between the injection direction and a normal direction of the injection hole wall surface in the airflow direction section of the combustion chamber. The first component value and the second component value both have the value range of 45-135 degrees.
Further, when the preset working range of the engine is Ma 2-4, the value range of the first component value is 45-115 degrees. When the preset engine working range is larger than Ma4, the value range of the first component value is 60-135 degrees.
Specifically, the first component a1 is shown in FIG. 5, where the arrow indicates the direction of injection and l1 is the distance between the orifice and the leading edge of the cavity. The setting direction of the spray holes is determined according to the working range value of the engine, the fuel injection effect can be further optimized, and better fuel mixing efficiency is obtained.
It should be understood that, although the steps in the flowchart of fig. 2 are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and described, and may be performed in other orders, unless explicitly stated otherwise. Moreover, at least a portion of the steps in fig. 2 may include multiple sub-steps or multiple stages that are not necessarily performed at the same time, but may be performed at different times, and the order of performance of the sub-steps or stages is not necessarily sequential, but may be performed in turn or alternately with other steps or at least a portion of the sub-steps or stages of other steps.
In one embodiment, a supersonic combustor fuel injection design device based on inlet non-uniform airflow is provided, comprising:
and the spray hole parameter calculation module is used for obtaining spray hole parameter values of spray holes in the combustion chamber according to preset supersonic speed air inlet channel parameters and engine parameters. The spray hole parameters comprise spray hole number, spray hole grouping data and spray hole aperture range values.
And the jet hole setting distance calculation module is used for obtaining the setting distance range value of the jet hole according to the preset fuel oil diffusion characteristic data and the preset fuel oil ignition delay characteristic data.
The nozzle setting angle and equivalent ratio calculation module is used for obtaining the distribution angle of the low-speed airflow region according to the airflow flow velocity circumferential characteristics of the airflow flowing to the section of the combustion chamber, obtaining the setting angle range value of the nozzle according to the distribution angle, and obtaining the global equivalent ratio of each group of nozzles according to the angle ratio of the distribution angle in the airflow flowing section.
And the fuel injection design module is used for obtaining fuel injection design data of the supersonic combustion chamber according to the jet hole parameter values, the set distance range values and the set angle range values of the jet holes and the global equivalent ratio of each group of jet holes.
In one embodiment, the jet hole parameter calculation module is used for acquiring preset supersonic speed air inlet channel parameters, engine working equivalence ratio parameters, engine stamping starting characteristic parameters and engine structure constraint parameters, and acquiring total fuel flow, jet hole number and jet hole grouping data of jet holes in the combustion chamber according to the acquired parameters. And obtaining the corresponding upper limit value of the fuel injection pressure, the average flow value of the single jet orifice and the upper limit flow value of the single jet orifice according to the structural constraint parameters of the engine, and calculating the range value of the jet orifice aperture according to the obtained values.
In one embodiment, the jet hole setting distance calculation module is used for calculating a jet hole aperture range value when the jet hole injects the gaseous fuel:
wherein j1 is the aperture range value of the spray orifice, mjIs the injection flow value of a single spray hole, gamma is the specific heat ratio of fuel, PjAt a gas injection pressure value, pjAnd the fuel density value is obtained.
In one embodiment, the nozzle hole setting distance calculation module is used for calculating a nozzle hole diameter range value when the nozzle hole injects the liquid fuel:
wherein j1 is the range value of the aperture of the spray orifice, v is fuel oilKinematic viscosity, K is the pipe diameter coefficient, mjInjection flow value, p, for a single orificejIs the fuel density value, DeltaPjThe injection pressure drop value is liquid.
In one embodiment, the nozzle setting angle and equivalent ratio calculation module is used for uniformly setting the first group of nozzles on the wall surface of the combustion chamber corresponding to the distribution angle to obtain the setting angle range value of the first group of nozzles. And uniformly arranging the rest spray holes on the wall surface of the combustion chamber outside the corresponding range of the distribution angle to obtain the range value of the arrangement angle of the spray holes and the grouped spray holes.
The specific definition of the supersonic combustor fuel injection design device based on the inlet non-uniform airflow can be referred to the definition of the supersonic combustor fuel injection design method based on the inlet non-uniform airflow, and is not described herein again. The modules in the supersonic combustor fuel injection design device based on the non-uniform air flow of the air inlet can be completely or partially realized by software, hardware and a combination thereof. The modules can be embedded in a hardware form or independent from a processor in the computer device, and can also be stored in a memory in the computer device in a software form, so that the processor can call and execute operations corresponding to the modules.
In one embodiment, a computer device is provided, which may be a terminal, and its internal structure diagram may be as shown in fig. 6. The computer device includes a processor, a memory, a network interface, a display screen, and an input device 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 and a computer program. The internal memory provides an environment for the operation of an operating system and computer programs in the non-volatile storage medium. 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 a supersonic combustor fuel injection design method based on port non-uniform airflow. The display screen of the computer equipment can be a liquid crystal display screen or an electronic ink display screen, and the input device of the computer equipment can be a touch layer covered on the display screen, a key, a track ball or a touch pad arranged on the shell of the computer equipment, an external keyboard, a touch pad or a mouse and the like.
Those skilled in the art will appreciate that the architecture shown in fig. 6 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, there is provided a computer device comprising a memory storing a computer program and a processor implementing the following steps when the processor executes the computer program:
and obtaining the spray hole parameter values of the spray holes in the combustion chamber according to preset supersonic speed air inlet channel parameters and engine parameters. The spray hole parameters comprise spray hole number, spray hole grouping data and spray hole aperture range values.
And obtaining a set distance range value of the jet hole according to preset fuel oil diffusion characteristic data and fuel oil ignition delay characteristic data.
The distribution angle of the low-speed airflow zone is obtained according to the airflow flow velocity circumferential characteristics of the airflow flowing to the cross section of the combustion chamber, the set angle range value of the spray holes is obtained according to the distribution angle, and the global equivalent ratio of each group of spray holes is obtained according to the angle proportion value of the distribution angle in the airflow flowing to the cross section.
And obtaining fuel injection design data of the supersonic combustion chamber according to the jet hole parameter values, the set distance range values and the set angle range values of the jet holes and the global equivalent ratio of each group of jet holes.
In one embodiment, the processor, when executing the computer program, further performs the steps of: the method comprises the steps of obtaining preset supersonic speed air inlet channel parameters, engine working equivalence ratio parameters, engine stamping starting characteristic parameters and engine structure constraint parameters, and obtaining total fuel flow, number of spray holes and spray hole grouping data of the spray holes in a combustion chamber according to the obtained parameters. And obtaining the corresponding upper limit value of the fuel injection pressure, the average flow value of the single jet orifice and the upper limit flow value of the single jet orifice according to the structural constraint parameters of the engine, and calculating the range value of the jet orifice aperture according to the obtained values.
In one embodiment, the processor, when executing the computer program, further performs the steps of: calculating the aperture range value of the spray hole:
wherein j1 is the aperture range value of the spray orifice, mjIs the injection flow value of a single spray hole, gamma is the specific heat ratio of fuel, PjAt a gas injection pressure value, pjAnd the fuel density value is obtained.
In one embodiment, the processor, when executing the computer program, further performs the steps of: calculating the aperture range value of the spray hole:
wherein j1 is the aperture range value of the spray orifice, v is the kinematic viscosity of the fuel oil, K is the pipe diameter coefficient, mjInjection flow value, p, for a single orificejIs the fuel density value, DeltaPjThe injection pressure drop value is liquid.
In one embodiment, the processor, when executing the computer program, further performs the steps of: and uniformly arranging the first group of spray holes on the wall surface of the combustion chamber corresponding to the distribution angle to obtain the range value of the arrangement angle of the first group of spray holes. And uniformly arranging the rest spray holes on the wall surface of the combustion chamber outside the corresponding range of the distribution angle to obtain the range value of the arrangement angle of the spray holes and the grouped spray holes.
In one embodiment, the processor, when executing the computer program, further performs the steps of: when the preset engine working range is Ma 2-4, the value range of the first component value is 45-115 degrees, and when the preset engine working range is larger than Ma4, the value range of the first component value is larger than 60-135 degrees.
In one embodiment, a computer-readable storage medium is provided, having a computer program stored thereon, which when executed by a processor, performs the steps of:
and obtaining the spray hole parameter values of the spray holes in the combustion chamber according to preset supersonic speed air inlet channel parameters and engine parameters. The spray hole parameters comprise spray hole number, spray hole grouping data and spray hole aperture range values.
And obtaining a set distance range value of the jet hole according to preset fuel oil diffusion characteristic data and fuel oil ignition delay characteristic data.
The distribution angle of the low-speed airflow zone is obtained according to the airflow flow velocity circumferential characteristics of the airflow flowing to the cross section of the combustion chamber, the set angle range value of the spray holes is obtained according to the distribution angle, and the global equivalent ratio of each group of spray holes is obtained according to the angle proportion value of the distribution angle in the airflow flowing to the cross section.
And obtaining fuel injection design data of the supersonic combustion chamber according to the jet hole parameter values, the set distance range values and the set angle range values of the jet holes and the global equivalent ratio of each group of jet holes.
In one embodiment, the computer program when executed by the processor further performs the steps of: the method comprises the steps of obtaining preset supersonic speed air inlet channel parameters, engine working equivalence ratio parameters, engine stamping starting characteristic parameters and engine structure constraint parameters, and obtaining total fuel flow, number of spray holes and spray hole grouping data of the spray holes in a combustion chamber according to the obtained parameters. And obtaining the corresponding upper limit value of the fuel injection pressure, the average flow value of the single jet orifice and the upper limit flow value of the single jet orifice according to the structural constraint parameters of the engine, and calculating the range value of the jet orifice aperture according to the obtained values.
In one embodiment, the computer program when executed by the processor further performs the steps of: calculating the aperture range value of the spray hole:
wherein j1 is the aperture range value of the spray orifice, mjIs the injection flow value of a single spray hole, gamma is the specific heat ratio of fuel, PjAt a gas injection pressure value, pjAnd the fuel density value is obtained.
In one embodiment, the computer program when executed by the processor further performs the steps of: calculating the aperture range value of the spray hole:
wherein j1 is the aperture range value of the spray orifice, v is the kinematic viscosity of the fuel oil, K is the pipe diameter coefficient, mjInjection flow value, p, for a single orificejIs the fuel density value, DeltaPjThe injection pressure drop value is liquid.
In one embodiment, the computer program when executed by the processor further performs the steps of: and uniformly arranging the first group of spray holes on the wall surface of the combustion chamber corresponding to the distribution angle to obtain the range value of the arrangement angle of the first group of spray holes. And uniformly arranging the rest spray holes on the wall surface of the combustion chamber outside the corresponding range of the distribution angle to obtain the range value of the arrangement angle of the spray holes and the grouped spray holes.
In one embodiment, the computer program when executed by the processor further performs the steps of: when the preset engine working range is Ma 2-4, the value range of the first component value is 45-115 degrees, and when the preset engine working range is larger than Ma4, the value range of the first component value is larger than 60-135 degrees.
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 may include non-volatile and/or volatile memory, among others. 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 Direct RAM (RDRAM), direct 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, which falls within the scope of protection of the present application. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (10)
1. A supersonic combustor fuel injection design method based on inlet non-uniform airflow is characterized by comprising the following steps:
acquiring a spray hole parameter value of a spray hole in the combustion chamber according to preset supersonic speed air inlet channel parameters and engine parameters; the spray hole parameters comprise spray hole number, spray hole grouping data and spray hole aperture range values;
obtaining a set distance range value of the jet hole according to preset fuel diffusion characteristic data and fuel ignition delay characteristic data;
obtaining a distribution angle of a low-speed airflow region according to the airflow flow velocity circumferential characteristics of the airflow flow direction section of the combustion chamber, obtaining a set angle range value of the spray holes according to the distribution angle, and obtaining the global equivalent ratio of each group of spray holes according to the angle ratio of the distribution angle in the airflow flow direction section;
and obtaining fuel injection design data of the supersonic combustion chamber according to the jet hole parameter values, the set distance range values and the set angle range values of the jet holes and the global equivalent ratio of each group of jet holes.
2. The method of claim 1, wherein the step of obtaining the nozzle hole parameter value of the nozzle hole in the combustion chamber according to the preset supersonic inlet channel parameter and the combustion chamber parameter comprises:
acquiring preset supersonic speed air inlet channel parameters, engine working equivalence ratio parameters, engine stamping starting characteristic parameters and engine structure constraint parameters, and acquiring total fuel flow, number of spray holes and spray hole grouping data of the spray holes in the combustion chamber according to the acquired parameters;
and obtaining a corresponding fuel injection pressure upper limit value, a single jet orifice average flow value and a single jet orifice upper limit flow value according to the engine structure constraint parameters, and calculating a jet orifice aperture range value according to the obtained values.
3. The method of claim 2, wherein said injection orifices inject gaseous fuel;
the calculation mode of the orifice aperture range value comprises the following steps:
wherein j1 is the aperture range value of the spray orifice, mjIs the injection flow value of a single spray hole, gamma is the specific heat ratio of fuel, PjAt a gas injection pressure value, pjAnd the fuel density value is obtained.
4. The method of claim 2, wherein said orifice injects liquid fuel;
the calculation mode of the orifice aperture range value comprises the following steps:
wherein j1 is the aperture range value of the spray orifice, v is the kinematic viscosity of the fuel oil, K is the pipe diameter coefficient, mjInjection flow value, p, for a single orificejIs the fuel density value, DeltaPjThe injection pressure drop value is liquid.
5. The method according to claim 1, wherein the manner of obtaining the set angle range value of the nozzle hole from the distribution angle includes:
uniformly arranging the first group of spray holes on the wall surface of the combustion chamber corresponding to the distribution angle to obtain the arrangement angle range value of the first group of spray holes;
and uniformly arranging the rest spray holes on the wall surface of the combustion chamber outside the corresponding range of the distribution angle to obtain the range value of the arrangement angle of the spray holes and the grouped spray holes.
6. The method of any one of claims 1 to 5, wherein the injection orifice parameter values further comprise a first component value of an angle between an injection direction and a wall of the combustion chamber in a flow direction, and a second component value of an angle between an injection direction and a normal to the wall of the injection orifice in a cross section of the flow direction of the combustion chamber; the value ranges of the first component value and the second component value are both 45-135 degrees.
7. The method of claim 6, wherein:
when the preset working range of the engine is Ma 2-4, the value range of the first component value is 45-115 degrees;
when the preset engine working range is larger than Ma4, the value of the first component value ranges from 60 degrees to 135 degrees.
8. A supersonic combustor fuel injection design device based on inlet non-uniform airflow is characterized by comprising:
the nozzle hole parameter calculation module is used for obtaining nozzle hole parameter values of nozzle holes in the combustion chamber according to preset supersonic speed air inlet channel parameters and engine parameters; the spray hole parameters comprise spray hole number, spray hole grouping data and spray hole aperture range values;
the nozzle setting distance calculation module is used for obtaining a setting distance range value of the nozzle according to preset fuel oil diffusion characteristic data and fuel oil ignition delay characteristic data;
the nozzle setting angle and equivalent ratio calculation module is used for obtaining the distribution angle of a low-speed airflow region according to the airflow velocity circumferential characteristics of the airflow flowing to the section of the combustion chamber, obtaining the setting angle range value of the nozzle according to the distribution angle, and obtaining the global equivalent ratio of each group of nozzles according to the angle ratio of the distribution angle in the airflow flowing section;
and the fuel injection design module is used for obtaining fuel injection design data of the supersonic combustion chamber according to the jet hole parameter values, the set distance range values and the set angle range values of the jet holes and the global equivalent ratio of each group of jet holes.
9. A computer device comprising a memory and a processor, the memory storing a computer program, wherein the processor implements the steps of the method of any one of claims 1 to 7 when executing the computer program.
10. A computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, carries out the steps of the method according to any one of claims 1 to 7.
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