CN116593168B - Method and system for evaluating fuel consumption rate of ramjet rotary detonation engine - Google Patents
Method and system for evaluating fuel consumption rate of ramjet rotary detonation engine Download PDFInfo
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
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Abstract
The invention provides a method and a system for evaluating the fuel consumption rate of a ramjet rotary detonation engine, which relate to the technical field of rotary detonation engines, and are characterized in that a test bed thrust test value and an engine exhaust end resistance of a test model engine are combined to calculate the net thrust of the test model engine, calculate the total pressure of a spray pipe outlet, calculate the flow of the engine according to the air flow and the fuel flow, obtain the whole engine thrust through the analysis of a pneumatic thermodynamic mathematical model, and calculate the fuel consumption rate according to the whole engine thrust and the fuel flow. The method realizes the fusion of test data and the aerodynamic mathematical model analysis method, has higher fuel consumption rate evaluation accuracy compared with a numerical simulation method, has simpler test process, shorter test period and lower test cost compared with a free jet test method, and is favorable for realizing quick and accurate iterative design of the engine.
Description
Technical Field
The invention relates to the technical field of rotary detonation engines, in particular to a method and a system for evaluating the fuel consumption rate of a stamping rotary detonation engine.
Background
Ramjet rotary detonation engines utilize a continuous efficient detonation process to organize the combustion process within a combustion chamber into which fuel and oxidizer are injected at one end, one or more detonation waves propagating circumferentially at the combustion chamber head to consume fresh mixture, and combustion products are expelled from a nozzle at high flow velocities to generate thrust. The mass of fuel consumed per hour to produce a unit thrust is known as the ramjet fuel consumption rate, an important parameter in determining the range and duration of an aircraft for assessing engine economy.
The current method for evaluating the fuel consumption rate of the ramjet rotary detonation engine is mainly divided into a numerical simulation mode and a free jet wind tunnel test mode. The accuracy of the numerical simulation mode is low, the free jet flow test period is long, the test process is complex, the test cost is high, and therefore the engine cannot be designed in a rapid iteration mode.
Disclosure of Invention
The invention aims to provide a method and a system for evaluating the fuel consumption rate of a ramjet rotary knock engine, which are used for solving the technical problems of low accuracy, complex test process, long time consumption and high cost of the fuel consumption rate evaluation of the ramjet rotary knock engine in the prior art.
In a first aspect, the method for evaluating the fuel consumption rate of the ramjet rotary knock engine provided by the invention comprises the following steps: test stand thrust test value combined with engineAnd engine exhaust end resistance +.>Calculating the net thrust of the engine +.>The method comprises the steps of carrying out a first treatment on the surface of the According to the formula->Calculating the engine flow +.>, wherein ,/>For air flow rate>Is the fuel flow; according to the formulaCalculating total pressure of the throat of the spray pipe>, wherein ,/>Is the specific heat ratio of fluid in the throat of the spray pipe, +.>Is the throat area of the spray pipe->For ambient pressure +.>Mach number of nozzle throat, critical state +.>The method comprises the steps of carrying out a first treatment on the surface of the According to the formulaCalculating total temperature of the throat of the spray pipe>, wherein ,/>R is the gas constant of the fluid in the throat of the spray pipe, < ->Is a relatively dense flow of the nozzle throat; calculating ideal exhaust contraction and expansionArea of nozzle outlet>Ideal exhaust expansion nozzle outlet static temperature +.>And the ideal exhaust convergent-divergent nozzle outlet velocity +.>The method comprises the steps of carrying out a first treatment on the surface of the According to the formulaCalculating the thrust of the whole engine>Under the assumption that the exhaust convergent-divergent nozzle is in the fully expanded state, the ideal convergent-divergent nozzle outlet pressure +.>，/>For ambient atmospheric pressure at the corresponding fly height,for the flight speed of an aircraft>The capture area of the air inlet channel; according to the formula->Calculating the fuel consumption rate of the engine。
With reference to the first aspect, the present invention provides a first possible implementation manner of the first aspect, wherein the test stand thrust test value of the combined engineAnd engine exhaust end resistance +.>Calculating the net thrust of the engine +.>The method comprises the following steps:
obtaining test bed thrust test value of ramjet rotary detonation engine on thrust test bedThe method comprises the steps of carrying out a first treatment on the surface of the During the stable propagation period of the detonation wave, the average pressure signal values of a plurality of radial positions of the tail end of the spray pipe are obtained>, wherein ,/>Numbering a plurality of radial positions of the nozzle tip, from a position close to the nozzle axis, in a direction gradually away from the nozzle axis in the radial direction of the nozzle +.>The values of (1) and (2) are 0, 1, 2 and 3 & ltn & gt respectively; according to the formula->Calculating the exhaust end resistance of the engine>，/>Is the resistance of the end of the inner ring of the spray pipe>Resistance is the end resistance of the outer ring of the spray pipe;
wherein ,numbering the maximum value of the pressure measuring points of the end face of the inner ring, < >>Numbering the maximum value of the pressure measuring points of the end face of the outer ring, +.>Is numbered->End radius corresponding to position ∈>；/>、/>、/> and />Number 1, number->Number->Number->End surface radius corresponding to the position of the pressure measuring point +.>For the distance between radially adjacent pressure measuring points on the end face of the inner ring, +.>For the distance between radially adjacent pressure measuring points on the outer ring end face, < > for>、/>、/>、/>Number 1, number->Number->Number->An average pressure value of the radial position of the pressure measuring point; according to the formula->Calculating the net thrust of the engine +.>。
With reference to the first possible implementation manner of the first aspect, the present invention provides a second possible implementation manner of the first aspect,wherein the average pressure signal value of a plurality of radial positions of the nozzle end is obtainedThe method comprises the following steps: obtaining pressure values of holes of multiple rows of test holes uniformly distributed in the circumferential direction of the spray pipe>Wherein i is the number of the row of the test holes along the circumferential direction of the spray pipe, and the value of i is 1 and 2 s respectively; according to the formula->Calculating the average pressure signal value +.>, wherein ,/>Is the sampling duration.
With reference to the first possible implementation manner of the first aspect, the present invention provides a third possible implementation manner of the first aspect, wherein the numbersThe distance between the pressure measuring point of (2) and the circumferential edge of the end face of the inner ring is +.>Number->The distance between the pressure measuring point of (2) and the circumferential edge of the end face of the outer ring is +.>。
With reference to the first aspect, the present invention provides a fourth possible implementation manner of the first aspect, wherein the calculating the ideal exhaust convergent-divergent nozzle outlet areaThe method comprises the following steps: according to the formula->Calculating the outlet area of an ideal exhaust convergent-divergent nozzle>, wherein ,/>Is the ideal gas specific heat ratio of the outlet of the exhaust convergent-divergent nozzle,for the ideal exhaust expansion-contraction nozzle outlet Mach number, < + >>，/>，/>Is the total pressure recovery coefficient of the exhaust nozzle +.>For the total pressure of the combustion chamber outlet,/->Is the throat area of the exhaust nozzle.
With reference to the first aspect, the present invention provides a fifth possible implementation manner of the first aspect, wherein the calculating the ideal exhaust convergent-divergent nozzle outlet static temperatureThe method comprises the following steps: according to the formula->Calculating the static temperature of the outlet of the ideal exhaust contraction and expansion spray pipe>, wherein ,/>Is the specific heat ratio of the fuel gas in the throat of the spray pipe.
With reference to the first aspect, the present invention provides a sixth possible implementation manner of the first aspect, wherein the calculating the ideal exhaust convergent-divergent nozzle outlet velocityThe method comprises the following steps: according to the formula->Calculating the outlet speed of ideal exhaust contraction and expansion spray pipe>。
In a second aspect, the present invention provides a ramjet engine fuel consumption rate evaluation system, which adopts the ramjet engine fuel consumption rate evaluation method according to the first aspect, and includes: thrust test bench for mounting a ramjet rotary detonation engine to obtain a test bench thrust test value of the engineThe method comprises the steps of carrying out a first treatment on the surface of the The multi-row static pressure detection groups are arranged at the tail end of the spray pipe and are arranged at intervals along the circumferential direction of the spray pipe, and each row of static pressure detection groups comprises a plurality of static pressure sensors which are arranged at intervals along the radial direction of the spray pipe; the main machine is used for calculating the total thrust +.of the test model engine>Thrust of whole engine>And engine fuel consumption->。
With reference to the second aspect, the present invention provides a first possible implementation manner of the second aspect, wherein the thrust testing stand includes: the device comprises a static frame, a movable frame, a thrust sensor, a floating support and an engine tool; the engine tool is arranged on the movable frame and is used for bearing a stamping rotary detonation engine; the bottom of the movable frame is connected with the floating support, and the floating support is arranged on the static frame; the thrust sensor is arranged on the static frame and is used for being abutted to the front end of the ramjet rotary detonation engine.
With reference to the second aspect, the present invention provides a second possible implementation manner of the second aspect, wherein each row of static pressure detection groups includes a plurality of static pressure sensors arranged at intervals along a radial direction of the nozzle; the static pressure sensors are numbered 0, 1, 2 in sequence along the direction of gradually separating from the axis of the spray pipe along the radial direction of the spray pipe from the position close to the axis of the spray pipe,······/>，/>The number of the maximum value is +.>Numbering the maximum value on the end face of the outer ring of the spray pipe; nozzle radius corresponding to the position of the static pressure sensor with the number 0 +.>Number 0 to number->Is uniformly spaced on the inner ring end face along the radial direction, the spacing between any two adjacent static pressure sensors on the inner ring end face is equal to the number ∈>The distances from the static pressure sensor to the circumferential edge of the end face of the inner ring are equalThe method comprises the steps of carrying out a first treatment on the surface of the Number->To number->Is uniformly spaced on the outer ring end face along the radial direction, the spacing between any two adjacent static pressure sensors on the outer ring end face is equal to the number +.>The distances from the static pressure sensor to the circumferential edge of the end face of the outer ring are equal.
The embodiment of the invention has the following beneficial effects: test bench thrust test values using combined engineAnd engine exhaust end resistance +.>Calculating net thrust +.>In accordance with the formula->Calculating the engine flow +.>, wherein ,/>For air flow rate>For fuel flow, according to the formula ∈ ->Calculating total pressure of throat of spray pipe, wherein ,/>Is the specific heat ratio of fluid in the throat of the spray pipe, +.>Is the throat area of the spray pipe->For ambient pressure +.>Mach number of nozzle throat, critical state +.>The method comprises the steps of carrying out a first treatment on the surface of the According to the formula->Calculating the total temperature of the throat of the spray pipe, wherein ,/>R is the gas constant of the fluid in the throat of the spray pipe, < ->Is a relatively dense flow of the nozzle throat; calculating the outlet area of ideal exhaust convergent-divergent nozzle>Ideal exhaust expansion nozzle outlet static temperature +.>And the ideal exhaust convergent-divergent nozzle outlet velocity +.>The method comprises the steps of carrying out a first treatment on the surface of the According to the formula->Calculating the thrust of the whole engine>Under the assumption that the exhaust convergent-divergent nozzle is in the fully expanded state, the ideal convergent-divergent nozzle outlet pressure +.>，/>For the ambient atmospheric pressure at the corresponding flight level, +.>For the flight speed of an aircraft>The capture area of the air inlet channel; according to the formulaCalculating the fuel consumption of the engine>. The method realizes the fusion of test data and the aerodynamic mathematical model analysis method, has higher fuel consumption rate evaluation accuracy compared with a numerical simulation method, has simpler test process, shorter test period and lower test cost compared with a free jet test method, and is favorable for realizing quick and accurate iterative design of the engine.
In order to make the above objects, features and advantages of the present invention more comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the related art, the drawings that are required to be used in the description of the embodiments or the related art will be briefly described, and it is apparent that the drawings in the description below are some embodiments of the present invention, and other drawings may be obtained according to the drawings without inventive effort for those skilled in the art.
FIG. 1 is a schematic diagram of a method for estimating fuel consumption of a ramjet rotary knock engine according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view of a ramjet rotary detonation engine provided by an embodiment of the present invention;
FIG. 3 is a right side view of a ramjet rotary detonation engine provided by an embodiment of the present invention;
fig. 4 is a schematic diagram of a thrust testing bench of a fuel consumption rate evaluation system of a ramjet rotary knock engine according to an embodiment of the invention.
Icon: 001-an inner barrel; 101-an inner ring end face; 002-outer cylinder; 201-an outer ring end face; 003-injection section; 004-diffuser; 005-flame chamber; 006-jet section; 007-a thermal jet initiator; 100-static frame; 200-moving frames; 300-push force sensor; 400-floating support; 500-engine tooling; 600-static pressure test group.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Physical quantities in the formulas, unless otherwise noted, are understood to be basic quantities of basic units of the international system of units, or derived quantities derived from the basic quantities by mathematical operations such as multiplication, division, differentiation, or integration.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Referring to fig. 2, the ramjet rotary knock engine includes: the inner cylinder 001 and the outer cylinder 002 are sleeved outside the inner cylinder 001, the inner cylinder 001 and the outer cylinder 002 are coaxial, and an annular chamber is formed between the inner cylinder 001 and the outer cylinder 002. The annular chamber is provided with an injection section 003, a diffusion section 004, a flame cavity 005 and an air injection section 006 in sequence along the axial direction, a thermal jet primer 007 is arranged at the position, close to the diffusion section 004, of the flame cavity 005, and 90 nozzle hole sites with the diameter of 0.2mm are arranged at intervals along the circumferential direction of the outer barrel 002 in the injection section 003. The outer diameter of the inner cylinder 001 of the diffusion section 004 is decreased along the air flow direction, the inner diameter of the outer cylinder 002 is increased along the air flow direction, the oil-gas mixture is taken as fuel gas to enter the flame cavity 005, the ignition and the detonation are carried out through a detonation device arranged on the outer cylinder 002, and the burnt gas is discharged through the air injection section 006.
As shown in fig. 1, the method for evaluating the fuel consumption rate of the ramjet rotary knock engine provided by the embodiment of the invention comprises the following steps:
test stand thrust test value combined with engineAnd engine exhaust end resistance +.>Calculating the net thrust of the engine +.>；
According to the formulaCalculating the engine flow +.>, wherein ,/>For air flow rate>Is the fuel flow;
according to the formulaCalculating total pressure of the throat of the spray pipe>, wherein ,/>Is the specific heat ratio of fluid in the throat of the spray pipe, +.>Is the throat area of the spray pipe->For ambient pressure +.>Mach number of nozzle throat, critical state +.>；
According to the formulaCalculating total temperature of the throat of the spray pipe>, wherein ,r is the gas constant of the fluid in the throat of the spray pipe, < ->Is a relatively dense flow of the nozzle throat;
calculating the outlet area of ideal exhaust contraction-expansion spray pipeIdeal exhaust expansion nozzle outlet static temperature +.>And the ideal exhaust convergent-divergent nozzle outlet velocity +.>；
According to the formulaCalculating the thrust of the whole engine>Under the assumption that the exhaust convergent-divergent nozzle is in the fully expanded state, the ideal convergent-divergent nozzle outlet pressure +.>，/>For the ambient atmospheric pressure at the corresponding flight level, +.>For the flight speed of an aircraft>The capture area of the air inlet channel;
according to the formulaCalculating the fuel consumption of the engine>。
When the test is carried out, the engine spray pipe is ensured to reach the critical state, and the thrust test value of the test bed is detected through the thrust test bedMeasuring the bottom pressure of the spray pipe by using a high-frequency static pressure sensor, and calculating the resistance +.>Analysis according to aerodynamic thermodynamic mathematical model to obtain the net thrust of the engine>. By adopting the method for evaluating the fuel consumption rate of the ramjet rotary detonation engine, the fusion of test data and the aerodynamic mathematical model analysis method is realized, the fuel consumption rate evaluation accuracy is higher compared with a numerical simulation method, the test process is simpler, the test period is shorter, the test cost is lower compared with a free jet test method, and the rapid and accurate iterative design of the engine is facilitated.
In the embodiment of the invention, the test bench thrust test value combined with the engineAnd engine exhaust end resistance +.>Calculating the net thrust of the engine +.>The method comprises the following steps:
obtaining test bed thrust test value of ramjet rotary detonation engine on thrust test bed；
Acquiring average pressure signal values of a plurality of radial positions of the tail end of the spray pipe in a stable propagation period of the detonation wave, wherein ,numbering multiple radial positions of nozzle tip, self-approachingThe position of the nozzle axis is gradually far from the nozzle axis along the radial direction of the nozzle +.>The values of (1) and (2) are 0, 1, 2 and 3 & ltn & gt respectively;
according to the formulaCalculating the exhaust end resistance of the engine>，/>Is the resistance of the tail end of the inner ring of the spray pipe,resistance is the end resistance of the outer ring of the spray pipe;
wherein ,the most number of the pressure measuring points of the inner ring end face (101)Big value (I)>The maximum value of the number of the pressure measuring points of the outer ring end face (201) is +.>Is numbered->End radius corresponding to position ∈>；/>、/>、/> and />Number 1, number->Number->Number->End surface radius corresponding to the position of the pressure measuring point +.>For the distance between radially adjacent pressure measuring points on the inner ring end face (101),. Sup.>For the distance between radially adjacent pressure measuring points on the outer ring end face (201)>、/>、、/>Number 1, number->Number->Number->An average pressure value of the radial position of the pressure measuring point;
according to the formulaCalculating the net thrust of the engine +.>。
In a possible embodiment, n=12, where eight pressure test points are located at the end of the inner barrel 001 of the ramjet rotary knock engine, and the other four pressure test points are located at the end of the outer barrel 002 of the ramjet rotary knock engine, and the 12 pressure test points are spaced apart along one radial direction of the nozzle, and the distances between adjacent pressure test points are uniformly distributed.
Further, the average pressure signal value of a plurality of radial positions of the tail end of the spray pipe is obtainedThe method comprises the following steps:
obtaining pressure values of various holes of multiple rows of test holes uniformly distributed in the circumferential direction of the spray pipeWherein i is the number of the row of the test holes along the circumferential direction of the spray pipe, and the value of i is 1 and 2 s respectively;
according to the formulaCalculating the average pressure signal value +.>, wherein ,is the sampling duration.
Further, an average pressure signal value p of a plurality of radial positions of the tail end of the spray pipe is obtained j The method comprises the following steps: obtaining pressure values p of holes of multiple rows of test holes uniformly distributed in the circumferential direction of the spray pipe i,j Wherein i is the number of the row of the test holes along the circumferential direction of the spray pipe, and the value of i is 1 and 2 s respectively; according to the formulaCalculating the average pressure signal value p for each radial position j Where Δt is the sampling duration.
The number of S can be increased as much as possible, so that the number of rows of test holes in the circumferential direction of the spray pipe is increased, the pressure test value sampling is further increased in the circumferential direction of the spray pipe, and the problem of space unsteadiness of static pressure measurement is solved by solving the pressure average value.
The pressure test points are sampled at high frequency by a pressure sensor, and the average pressure signal value p of each radial position is obtained by time-averaging static pressure of a plurality of periods j Can solve the problem of unsteady static pressure measurement side time, and further can make the resistance of the exhaust end of the engineThe calculation is more accurate.
Further, the numberThe distance between the pressure measuring point of (1) and the circumferential edge of the inner ring end face (101) is +.>Number->The distance between the pressure measuring point of (2) and the circumferential edge of the outer ring end face (201) is +.>。
Further, the ideal exhaust contraction and expansion spray pipe outlet area is calculatedThe method comprises the following steps:
according to the formulaCalculating the outlet area of ideal exhaust contraction and expansion spray pipe, wherein ,/>Is the gas specific heat ratio of the outlet of the ideal exhaust convergent-divergent nozzle, +.>For the ideal exhaust expansion-contraction nozzle outlet Mach number, < + >>，/>，/>Is the total pressure recovery coefficient of the exhaust nozzle +.>For the total pressure of the combustion chamber outlet,/->Is the throat area of the exhaust nozzle.
Further, the calculation is idealStatic temperature of outlet of exhaust expansion jet pipeThe method comprises the following steps: according to the formulaCalculating the static temperature of the outlet of the ideal exhaust contraction and expansion spray pipe>, wherein ,/>Is the specific heat ratio of the fuel gas in the throat of the spray pipe.
Further, the ideal exhaust contraction and expansion nozzle outlet speed is calculatedThe method comprises the following steps: according to the formulaCalculating the outlet speed of ideal exhaust contraction and expansion spray pipe>。
Solving nozzle outlet speed through aerodynamic thermodynamic mathematical modelBy measuring or detecting the flying speed of the aircraft>Air flow rate->Intake duct capture area->The method comprises the steps of carrying out a first treatment on the surface of the The method realizes the fusion of the thrust test and the aerodynamic mathematical model analysis method, has higher fuel consumption rate evaluation accuracy compared with a numerical simulation method, and has simpler test process, shorter test period and test period compared with a free jet test methodThe cost is lower, and the quick and accurate iterative design of the engine is facilitated.
As shown in fig. 3 and 4, the fuel consumption rate evaluation system of a ramjet rotary knock engine provided by the embodiment of the invention includes:
thrust test bench for mounting a ramjet rotary detonation engine to obtain a test bench thrust test value for a test model engine；
The multi-row static pressure detection groups 600 are arranged at the tail end of the spray pipe and are arranged at intervals along the circumferential direction of the spray pipe, and each row of static pressure detection groups 600 comprises a plurality of static pressure sensors which are arranged at intervals along the radial direction of the spray pipe;
the main machine, the thrust test bench and the plurality of static pressure sensors are respectively connected with the main machine, and the main machine is used for executing a program corresponding to the fuel consumption rate evaluation method of the ramjet rotary detonation engine according to any one of the embodiments, so as to calculate the total thrust of the test model engineThrust of whole engine>And engine fuel consumption->。
By adopting the stamping rotary detonation engine fuel consumption rate evaluation system, the fusion of test data and a pneumatic thermodynamic mathematical model analysis method is realized, compared with a numerical simulation method, the fuel consumption rate evaluation accuracy is higher, compared with a free jet test method, the test process is more concise, the test period is shorter, the test cost is lower, and the rapid and accurate iterative design of the engine is facilitated. The multiple rows of static pressure detection groups 600 are arranged at intervals along the circumferential direction of the spray pipe, each row of static pressure detection groups 600 comprises a plurality of static pressure sensors arranged at intervals along the radial direction of the spray pipe, and static pressure average value calculation is carried out in time and space, so that the problem of time and space unsteadiness of static pressure measurement is solved, and further, the static pressure measurement can be carried outThe resistance calculation at the bottom of the engine is more accurate, thereby improving the thrust of the whole engineIs beneficial to improving the accuracy of the subsequent fuel consumption rate.
As shown in fig. 4, in the embodiment of the present invention, the thrust test stand includes: the device comprises a static frame 100, a movable frame 200, a thrust sensor 300, a floating support 400 and an engine tool 500; the engine tool 500 is mounted on the movable frame 200, and the engine tool 500 is used for bearing a ramjet rotary detonation engine; the bottom of the movable frame 200 is connected with a floating support 400, and the floating support 400 is arranged on the static frame 100; the stationary frame 100 is mounted with a thrust sensor 300, and the thrust sensor 300 is used for abutting against the front end of the ramjet rotary detonation engine. Wherein the floating support 400 includes a plate spring or a spring, is disposed along the bottom surface of the movable frame 200 at intervals by a plurality of floating supports 400, and supports the movable frame 200 together by the plurality of floating supports 400. When the ramjet rotary detonation engine is started, the movable frame 200 can move in the horizontal direction relative to the static frame 100, the front end of the ramjet rotary detonation engine impacts the thrust sensor 300, and the pressure born by the thrust sensor 300 is used as a test bed thrust test valueTo provide an accurate input for the subsequent calculation of fuel consumption.
Further, the ramjet fuel consumption rate evaluation system is particularly suitable for a ramjet rotary knock engine provided with a convergent nozzle, and further comprises a flowmeter mounted on a fuel pipeline, wherein the flowmeter is connected with a host. The flowmeter adopts a turbine flowmeter for measuring the fuel flow entering the engine。
In addition, the fuel consumption rate evaluation system of the ramjet rotary detonation engine further comprises an interaction device, and the interaction device is connected with the host. The interaction means comprise a display, an input device, a communication means, etc., on the one hand known parameters can be entered,for example: input flying speedAir mass flow->Fuel mass flow->Intake duct capture area->Area of throat of nozzle->Area of nozzle outlet->Ground atmospheric pressure during test ++>Atmospheric pressure at the corresponding flying height +.>And the total pressure recovery coefficient of the spray pipe->The method comprises the steps of carrying out a first treatment on the surface of the On the other hand, the interactive means may output the calculated engine fuel consumption +.>。
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (7)
1. A method for evaluating the fuel consumption rate of a ramjet rotary knock engine is characterized by comprising the following steps:
test stand thrust test value combined with engineAnd engine exhaust end resistance +.>Calculating the net thrust of the engine +.>, wherein ,/>；
According to the formulaCalculating the engine flow +.>, wherein ,/>For air flow rate>Is the fuel flow;
according to the formulaCalculating total pressure of the throat of the spray pipe>, wherein ,/>Is the specific heat ratio of fluid in the throat of the spray pipe, +.>Is the throat area of the spray pipe->For ambient pressure +.>Mach number of nozzle throat, critical state +.>；
According to the formulaCalculating total temperature of the throat of the spray pipe>, wherein ,/>R is the gas constant of the fluid in the throat of the spray pipe, < ->Is a relatively dense flow of the nozzle throat;
calculating the outlet area of ideal exhaust contraction-expansion spray pipeIdeal exhaust expansion nozzle outlet static temperature +.>And the ideal exhaust convergent-divergent nozzle outlet velocity +.>The method comprises the steps of carrying out a first treatment on the surface of the The outlet area of the ideal exhaust convergent-divergent nozzle is calculated>The method comprises the following steps: according to the formulaCalculating the outlet area of an ideal exhaust convergent-divergent nozzle>, wherein ,/>Is the gas specific heat ratio of the outlet of the ideal exhaust convergent-divergent nozzle, +.>For the ideal exhaust convergent-divergent nozzle exit mach number,，/>，/>is the total pressure recovery coefficient of the exhaust nozzle +.>For the total pressure of the combustion chamber outlet,/->Is the throat area of the exhaust nozzle; the outlet static temperature of the ideal exhaust expansion nozzle is calculated>The method comprises the following steps: according to the formula->Calculating the static temperature of the outlet of the ideal exhaust contraction and expansion spray pipe>, wherein ,/>The specific heat ratio of the fuel gas in the throat of the spray pipe; the outlet speed of the ideal exhaust convergent-divergent nozzle is calculated>The method comprises the following steps: according to the formulaCalculating the outlet speed of ideal exhaust contraction and expansion spray pipe>；
According to the formulaCalculating the thrust of the whole engine>Under the assumption that the exhaust convergent-divergent nozzle is in the fully expanded state, the ideal convergent-divergent nozzle outlet pressure +.>，/>For the ambient atmospheric pressure at the corresponding flight level, +.>For the flight speed of an aircraft>The capture area of the air inlet channel;
according to the formulaCalculating the fuel consumption of the engine>。
2. The method for evaluating fuel consumption rate of ramjet rotary knock engine according to claim 1, characterized in that the test stand thrust test value of the combined engineAnd engine exhaust end resistance +.>Calculating the net thrust of the engine +.>The method comprises the following steps:
obtaining test bed thrust test value of ramjet rotary detonation engine on thrust test bed；
Acquiring average pressure signal values of a plurality of radial positions of the tail end of the spray pipe in a stable propagation period of the detonation wave, wherein ,/>Numbering a plurality of radial positions of the nozzle tip, from a position close to the nozzle axis, in a direction gradually away from the nozzle axis in the radial direction of the nozzle +.>The values of (1) and (2) are 0, 1, 2 and 3 & ltn & gt respectively;
according to the formulaCalculating the exhaust end resistance of the engine>，/>Is the resistance of the tail end of the inner ring of the spray pipe,resistance is the end resistance of the outer ring of the spray pipe;
wherein ,the maximum value of the pressure measuring point number of the inner ring end face (101) is +.>The maximum value of the number of the pressure measuring points of the outer ring end face (201) is +.>Is numbered->End radius corresponding to position ∈>；/>、/>、/> and />Number 1, number->Number->Number->End surface radius corresponding to the position of the pressure measuring point +.>For the distance between radially adjacent pressure measuring points on the inner ring end face (101),. Sup.>For the distance between radially adjacent pressure measuring points on the outer ring end face (201)>、/>、/>、/>Number 1, number->Number->Number->Average pressure value at radial position of pressure measuring point.
3. The method for estimating fuel consumption of a ramjet rotary detonation engine according to claim 2, wherein said average pressure signal values for a plurality of radial positions of a nozzle tip are obtainedThe method comprises the following steps:
obtaining pressure values of various holes of multiple rows of test holes uniformly distributed in the circumferential direction of the spray pipeWherein i is the number of the row of the test holes along the circumferential direction of the spray pipe, and the value of i is 1 and 2 s respectively;
according to the formulaCalculating the average pressure signal value +.>, wherein ,/>Is the sampling duration.
4. The method for estimating fuel consumption of ramjet rotary knock engine according to claim 2 or 3, characterized by numberingThe distance between the pressure measuring point of (1) and the circumferential edge of the inner ring end face (101) is +.>Number->The distance between the pressure measuring point of (2) and the circumferential edge of the outer ring end face (201) is +.>。
5. A ramjet engine fuel consumption rate evaluation system, characterized in that it employs the ramjet engine fuel consumption rate evaluation method according to any one of claims 1 to 4, and comprises:
thrust test bench for mounting a ramjet rotary detonation engine to obtain a test bench thrust test value of the engine；
The multi-row static pressure detection groups (600) are arranged at the tail end of the spray pipe and are arranged at intervals along the circumferential direction of the spray pipe, and each row of static pressure detection groups (600) comprises a plurality of static pressure sensors which are arranged at intervals along the radial direction of the spray pipe;
the main machine, the thrust test bench and the static pressure sensors are respectively connected with the main machine, and the main machine is used for calculating the total thrust of the test model engineThrust of whole engine>And engine fuel consumption->。
6. The ramjet rotary knock-out engine fuel consumption rate estimation system according to claim 5, wherein the thrust test bench comprises: the device comprises a static frame (100), a movable frame (200), a thrust sensor (300), a floating support (400) and an engine tool (500);
the engine tool (500) is mounted on the movable frame (200), and the engine tool (500) is used for bearing a ramjet rotary detonation engine;
the bottom of the movable frame (200) is connected with the floating support (400), and the floating support (400) is arranged on the static frame (100);
the static frame (100) is provided with the thrust sensor (300), and the thrust sensor (300) is used for being abutted against the front end of the ramjet rotary detonation engine.
7. The ramjet rotary knock engine fuel consumption rate estimation system according to claim 5, wherein each row of the static pressure detection groups (600) includes a plurality of static pressure sensors arranged at intervals in a nozzle radial direction;
the static pressure sensors are numbered 0, 1, 2 in sequence along the direction of gradually separating from the axis of the spray pipe along the radial direction of the spray pipe from the position close to the axis of the spray pipe,······/>，/>The maximum value of the number on the inner ring end face (101) of the spray pipe is +.>Numbering the maximum value on the outer ring end surface (201) of the spray pipe; nozzle radius corresponding to the position of the static pressure sensor with the number 0 +.>Number 0 to number->Is uniformly spaced on the inner ring end face (101) along the radial direction, the spacing between any two adjacent static pressure sensors on the inner ring end face (101) is equal to the number>The distances from the static pressure sensor to the circumferential edge of the inner ring end face (101) are equal; number->To number->Is uniformly spaced on the outer ring end surface (201) along the radial direction, the spacing between any two adjacent static pressure sensors on the outer ring end surface (201), and the numberThe spacing from the static pressure sensor to the circumferential edge of the outer ring end surface (201) is equal.
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