CN106545411B - Simulate the design method of the direct-connected experimental rig of Distorted Flow Field - Google Patents
Simulate the design method of the direct-connected experimental rig of Distorted Flow Field Download PDFInfo
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- 238000002955 isolation Methods 0.000 claims description 79
- 238000011161 development Methods 0.000 claims description 40
- 238000012360 testing method Methods 0.000 claims description 37
- 239000007921 spray Substances 0.000 claims description 24
- 238000005259 measurement Methods 0.000 claims description 18
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- 238000002485 combustion reaction Methods 0.000 abstract description 2
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
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Abstract
The hypersonic interior direct-connected experimental rig i.e. design method for rotating into air flue circle distance piece Distorted Flow Field is simulated the invention discloses a kind of, the flow field structure closer to real working condition can be provided for combustion chamber.Experimental rig of the present invention mainly includes：Jet pipe, boundary-layer developed regime, distort generator, circular distance piece.Using the distance piece flow field of inlets as target flow field, the shape face for the generator that distorted according to distance piece entrance flow Field Design, segment length and design jet pipe shape face are developed according to the parameters selection boundary-layer in distortion generator inlet section.Numerical computations are made to the direct-connected experimental rig, make appropriate amendment according to the error in target flow field.This circular direct-connected experiment of distance piece provided by the invention can be good at simulating the flow distortion situation under true flow field, and existing " to whirlpool " flow behavior, is of great importance to the research under later stage Distorted Flow Field particularly in distance piece.Device design is simple, and experimentation cost is low, simulates effect stability.
Description
Technical Field
The invention belongs to the technical field of hydromechanics, and particularly relates to a direct connection test device for simulating a distorted flow field of a hypersonic speed inward-turning air inlet channel-circular isolation section and a design method.
Background
The circular isolation section with the air inlet passage has great distortion, and if the inner turning air inlet passage is connected with the circular isolation section, an obvious vortex-pair structure can be formed. However, the direct connection test for the circular isolation section test is usually a uniform inflow working condition, an equal-straight boundary layer development section is connected behind the spray pipe, and the isolation section is connected behind the development section. There is also a literature that a test simulation device is made for the asymmetry of the boundary layer of the rectangular isolation section, but the mutual interference effect of shock waves/expansion waves in a flow field is not simulated. Therefore, the design of the isolation section test device capable of simulating the flow field distortion of the inlet of the isolation section is particularly important, if the device can enable the direct-connection engine test to be closer to the free jet test flow field with the air inlet passage isolation section, the test cost can be greatly reduced, and the device has great significance for the research under the later-stage distorted flow field.
Disclosure of Invention
The purpose of the invention is as follows: in order to overcome the defects in the prior art, the invention provides a direct connection test device for simulating a distorted flow field of a hypersonic speed internal rotation air inlet channel-circular isolation section and a design method.
The technical scheme of the invention is summarized as follows:
1) according to the parameters of the outlet flow field of the target air inlet channel, including the mass average Mach numberFlow field distortion index D, Mach number distortion index DMaEtc., designing a distortion generator profile;
2) selecting a proper boundary layer development segment length according to the geometric structure of the distortion generator;
3) selecting a proper spray pipe according to the inlet parameters of the distortion generator;
4) and (3) finely adjusting the outlet parameters of the spray pipe, so that the error between the outlet parameters of the distortion generator and the parameters of the target inlet passage outlet is reduced to be within an allowable range.
The technical scheme is as follows: in order to achieve the purpose, the invention adopts the technical scheme that:
a direct connection test device for simulating a distorted flow field of a hypersonic speed inward-turning air inlet channel-circular isolation section comprises a spray pipe, a boundary layer development section, a distortion generator and a circular isolation section which are sequentially connected end to end in a direct connection mode, wherein an outlet profile at the tail end of the spray pipe is connected with an inlet of the boundary layer development section in a matching mode, an outlet profile of the boundary layer development section is connected with an inlet of the distortion generator in a matching mode, and an outlet profile of the distortion generator is connected with an inlet of the circular isolation section in a matching mode; and an inlet of the circular isolation section is provided with an air inlet channel.
A design method of a direct connection test device for simulating a distorted flow field of a hypersonic speed inward turning air inlet channel-circular isolation section comprises the following steps:
(1) taking an isolation section with an air inlet channel as a target flow field, and extracting parameters of an initial section of the target flow field, namely an inlet section of the isolation section;
(2) designing the shape surface of the distortion generator according to the parameter of the inlet section of the isolation section;
(3) designing the length of the boundary layer development section according to the initial section parameters of the distortion generator, the thickness and the distribution of the boundary layer at the entrance of the isolation section;
(4) carrying out numerical simulation on a model consisting of the boundary layer development section, the distortion generator and the isolation section to obtain an inlet parameter of the boundary layer development section, carrying out shape surface design on the spray pipe according to the inlet parameter, and correcting the length of the boundary layer development section by considering the boundary layer effect of the spray pipe;
(5) performing numerical simulation on a model consisting of the spray pipe, the boundary layer development section, the distortion generator and the isolation section, calculating section parameters and wall surface pressure distribution conditions of the isolation section, and comparing the section parameters and the wall surface pressure distribution conditions with a target flow field;
(6) and adjusting and correcting the profile design of the test device according to the deviation from the target flow field, and repeating the steps until the simulation result meets the design requirement.
Further, in the step (1), a numerical simulation software is used for calculating a free jet flow field of the circular isolation section with the air inlet channel, and required parameters including mach numbers of an inlet and an outlet of the isolation section, the thickness of a boundary layer, static pressure, temperature, flow field distortion and mach number distortion and the wall surface pressure distribution condition of the isolation section are obtained.
Further, the non-uniformity degree D of the Mach number of the outlet of the isolation sectionMaThe expression is as follows:
wherein,-mass average mach number; mai-mach number at each measurement point; a. thei-the area of each measurement point;-mass flow at each measurement point; a. the0-measuring the total area of the cross section;-measuring the total mass flow of the cross section; n-dividing the measuring section into N small areas.
Further, the flow field distortion index D is represented by a total mass flow in a non-dimensionalized manner as follows:
wherein ρ -total fluid density of the measurement cross section; u-main flow direction velocity of the measurement section, piDensity of fluid at each measurement point, ui-the speed of the main flow direction at each measuring point,for the mass flow of the respective measuring points, A0To measure the total area of the cross section;to measure the total mass flow of the cross section.
Further, in the step (2), a specific design method of the distortion generator is as follows:
1) obtaining a target flow field, namely the characteristics of a target air inlet under a typical working condition, including a flow field structure, parameter distribution and overall performance;
2) extracting parameters of the cross section of the air inlet channel throat of the target flow field;
3) designing a distortion generation shape line;
4) adjusting parameters of the inlet flow field of the distortion generator, the parameters including the mass average Mach numberFlow field distortion index D, Mach number distortion index DMa(ii) a Determining the length of the boundary layer development section according to the boundary layer thickness of the inlet of the isolation section, and adjusting the outlet Mach of the spray pipe on the basis of determining the boundary layer development sectionThe error between the flow field parameter of the inlet of the distortion generator and the cross section parameter of the throat of the air inlet channel of the target flow field is within an allowable range, namely within 6 percent of the error;
5) and selecting the total airflow deflection angle from the boundary layer development section to the circular isolation section according to the geometric configuration of the inward turning air inlet channel of the target flow field.
Further, in the step (4), the inlet parameters of the boundary layer development section include mass average mach number, flow field distortion index, mach number distortion index, static pressure and temperature.
Further, in the step (4), a nozzle with a proper shape surface is selected according to the inlet parameters and the flow relation of the boundary layer development section, and the outlet parameters of the nozzle comprise outlet mach number, outlet area, static pressure, total pressure and temperature.
Has the advantages that: the direct connection test device and the design method for simulating the distorted flow field of the hypersonic speed inward-turning air inlet channel-circular isolation section can well simulate the flow field distortion condition under a real flow field, particularly the flow characteristic of the opposite vortex existing in the isolation section, and have great significance for the research under the later distorted flow field. The device has simple design, low test cost and stable simulation effect.
Drawings
FIG. 1 is a schematic diagram of a test device capable of simulating a distorted flow field of an isolation section.
FIG. 2 is a schematic diagram of a typical internal turn intake and circular isolation section.
Wherein: 1-a spray pipe; 2-boundary layer development section; 3-a distortion generator; 4-a circular isolation section; 5-internal rotation air inlet channel (square to round); 6-throat section (insulation section entrance section); 7-target model circular isolated segment; 8-section of the outlet of the separation section.
Detailed Description
The present invention will be further described with reference to the accompanying drawings.
The invention relates to a direct connection test device for simulating a distorted flow field of a hypersonic speed inward turning air inlet channel-circular isolation section and a design method, which can provide a flow field structure closer to a real working condition for a combustion chamber. The test device of the invention mainly comprises: the device comprises a spray pipe 1, a boundary layer development section 2, a distortion generator 3 and a circular isolation section 4. The method comprises the steps of taking an isolation section flow field with an air inlet channel as a target flow field, designing the shape of a distortion generator according to an isolation section inlet flow field, and selecting the length of a boundary layer development section and designing the shape of a spray pipe according to parameters of a distortion generator inlet section. And (4) carrying out numerical calculation on the direct connection test device, and carrying out appropriate correction according to the error of the direct connection test device and a target flow field. The circular isolation section direct connection test provided by the invention can well simulate the flow field distortion condition under a real flow field, and particularly has the flow characteristic of 'vortex pair' existing in the isolation section, thereby having great significance for the research under the later distorted flow field. The device has simple design, low test cost and stable simulation effect.
A test device capable of simulating a distorted flow field of an isolation section selects a proper distortion generator according to a given isolation section flow field with an air inlet channel, namely a target flow field, and selects a boundary layer development section and a spray pipe accordingly.
The method specifically comprises the following steps:
(1) for the flow field distortion in the circular isolation section 4 with the air inlet passage to be simulated, numerical simulation software can be used for calculating the free jet flow field of the isolation section with the air inlet passage to obtain required parameters, such as Mach number, boundary layer thickness, static pressure, temperature, flow field distortion, Mach number distortion and the like of the inlet and the outlet of the circular isolation section 4, and the wall surface pressure distribution condition of the circular isolation section.
(2) A proper distortion generator 3 shape line design method is selected according to the inlet parameters of the circular isolation section 4, a boundary layer development section 2 with a proper length is selected according to the thickness of a boundary layer of an inlet of the circular isolation section 4 (the thickness of the boundary layer is approximately in a linear relation with the length of the boundary layer development section, and the length of the boundary layer development section can be selected according to the existing primarily selected model simulation result), and a proper distortion generator 3 wave system configuration is selected according to the target flow field shock wave configuration condition and the wall surface pressure distribution condition.
(3) And performing numerical simulation on a model consisting of the boundary layer development section 2, the distortion generator 3 and the circular isolation section 4 to obtain inlet parameters including Mach number, static pressure, temperature and the like of the boundary layer development section 2, selecting a proper spray pipe 1 surface design method according to the parameters, and correcting the length of the boundary layer development section 2 by considering the boundary layer effect of the spray pipe 1.
(4) And (3) performing numerical simulation on a model (shown in figure 1) consisting of the spray pipe 1, the boundary layer development section 2, the distortion generator 3 and the circular isolation section 4, calculating parameters of each section of the isolation section 4 and the distribution condition of wall surface pressure, and comparing the parameters with a target flow field.
(5) And (4) correcting each part according to the error between the simulation result and the real result, and repeating the design processes of (2), (3) and (4) until the simulation result meets the design requirement.
Examples
The invention is further illustrated below with reference to an example.
In order to quantitatively measure the quality of the outlet flow field, a distortion index D is defined to measure the change of the momentum of the outlet, and the total mass flow is used for carrying out dimensionless operation. The expression is as follows:
wherein ρ -total fluid density of the measurement cross section; u. ofMeasuring the velocity of the main flow direction of the cross section, piDensity of fluid at each measurement point, ui-the speed of the main flow direction at each measuring point,for the mass flow of the respective measuring points, A0To measure the total area of the cross section;to measure the total mass flow of the cross section. The whole section is calculated by adopting a discrete method, namely the section is divided into a plurality of small areas, and the parameter value of each small area is synthesized into the parameter value of the whole section.
Further, D is defined hereinMaTo describe the non-uniformity degree of the Mach number of the circular isolating section outlet section 8, the expression is as follows:
in the formula:
wherein,-mass average mach number; mai-mach number at each measurement point; a. thei-the area of each measurement point;-mass flow at each measurement point; a. the0-measuring the total area of the cross section; m-measuring the total mass flow of the cross section; n-dividing the measuring section into N small areas. The whole section is calculated by adopting a discrete method, namely the section is divided into a plurality of small areas, and the parameter value of each small area is synthesized into the parameter value of the whole section.
In the embodiment, the performance of a circular isolation section Ma5 connected behind a certain type of square-to-circular inner-turning air inlet 5 under the working condition is used as a target flow field, and according to the calculation formula, the mass average Mach number of the inlet section, namely the throat section 6, of the target model circular isolation section 7 is 2.65, the flow field distortion is 0.2382, the Mach number distortion is 0.17998, the mass average Mach number of the outlet of the isolation section is 2.276, the flow field distortion is 0.29708, the Mach number distortion is 0.2056, and the total pressure recovery coefficient of the isolation section is 0.80352. According to the design method, two distortion generator models with better performance are designed, performance parameters are shown in table 1, wherein O is a target model, Modela and Modela are distortion generator models, it can be seen that errors of the model Modela throat and outlet section parameters and a target flow field are slightly larger, the maximum error is 6.1%, the design requirements are basically met, errors of the Modela throat and outlet section parameters and the target flow field are smaller, the maximum error is 2.3%, and the model belongs to a model with better simulation effect. The simulation results of the Model A and the Model B can be well matched with the target flow field.
TABLE 1 Ma5 Condition section Performance parameters
On the premise that the Ma5 working condition meets the design requirement, the two models are subjected to numerical calculation of the Ma6 working condition, the simulation result is shown in Table 2, the result shows that the two given test devices also have good matching effect under the Ma6 working condition, the error of each parameter is kept within 6%, the requirement of a general design error range is met, and the distortion generator can meet the wide Mach number working range.
TABLE 2 Ma6 Condition section Performance parameters
From the comparison results, the calculation result of the isolated section flow field simulation device is well matched with the target flow field.
The method has the advantages that the literature about the effect of introducing the distorted flow field in the direct connection test of the isolation section is less, a system research direction is not provided in China at present, particularly for the circular isolation section, an inward turning air inlet channel needs to be configured, and a new air inlet channel design method in China is provided, so that the method for simulating the flow field of the inward turning air inlet channel has no more literature which can be referred to. The invention makes up the defects in the test field and provides important basis for the direct connection test of the engine under complex conditions.
The above description is only of the preferred embodiments of the present invention, and it should be noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the invention and these are intended to be within the scope of the invention.
Claims (7)
1. A design method for simulating a direct connection test device of an inward turning air inlet channel-circular isolation section distortion flow field is characterized by comprising the following steps: the direct connection test device comprises a spray pipe (1), a boundary layer development section (2), a distortion generator (3) and a circular isolation section (4) which are connected end to end in sequence, wherein an outlet profile at the tail end of the spray pipe (1) is connected with an inlet of the boundary layer development section (2) in a matching mode, an outlet profile of the boundary layer development section (2) is connected with an inlet of the distortion generator (3) in a matching mode, and an outlet profile of the distortion generator (3) is connected with an inlet of the circular isolation section (4) in a matching mode; an inlet of the circular isolation section (4) is provided with an air inlet channel;
the design method of the direct connection test device comprises the following steps:
(1) taking the circular isolation section (4) with the air inlet channel as a target flow field, and extracting parameters of the initial section of the target flow field, namely the inlet section of the circular isolation section (4);
(2) designing the shape surface of the distortion generator according to the parameters of the inlet section of the circular isolation section (4) and the parameters of the inlet of the circular isolation section (4);
(3) designing the length of the boundary layer development section (2) according to the initial section parameters of the distortion generator (3), the thickness and distribution of the boundary layer at the inlet of the circular isolation section (4);
(4) carrying out numerical simulation on a model consisting of the boundary layer development section (2), the distortion generator (3) and the circular isolation section (4) to obtain an inlet parameter of the boundary layer development section (2), carrying out the shape design of the spray pipe (1) according to the inlet parameter, and correcting the length of the boundary layer development section (2) by considering the boundary layer effect of the spray pipe;
(5) performing numerical simulation on a model consisting of the spray pipe (1), the boundary layer development section (2), the distortion generator (3) and the circular isolation section (4), calculating each section parameter and wall surface pressure distribution condition of the circular isolation section (4), and comparing the section parameters and the wall surface pressure distribution condition with a target flow field;
(6) and (5) adjusting and correcting the profile design of the direct connection test device according to the deviation from the target flow field, and repeating the steps (1) to (5) until the simulation result meets the design requirement.
2. The design method of the direct connection test device for simulating the distortion flow field of the internal turning air inlet channel-circular isolation section according to claim 1 is characterized in that: in the step (1), a numerical simulation software is used for calculating a free jet flow field of the circular isolation section (4) with the air inlet channel, and required parameters including Mach number of an inlet and an outlet of the circular isolation section, thickness of a boundary layer, static pressure, temperature, flow field distortion and Mach number distortion and wall surface pressure distribution of the circular isolation section (4) are obtained.
3. The simulated internal transfer duct-circular septum of claim 2The design method of the direct connection test device of the off-segment distortion flow field is characterized in that: the non-uniformity degree D for the Mach number of the circular isolation section outletMaExpressed, the expression is as follows:
<mrow> <msub> <mi>D</mi> <mrow> <mi>M</mi> <mi>a</mi> </mrow> </msub> <mo>=</mo> <mrow> <mo>(</mo> <munderover> <mi>&Sigma;</mi> <mrow> <mi>i</mi> <mo>=</mo> <mn>1</mn> </mrow> <mi>N</mi> </munderover> <mo>|</mo> <mrow> <msub> <mi>Ma</mi> <mi>i</mi> </msub> <mo>-</mo> <mover> <mrow> <mi>M</mi> <mi>a</mi> </mrow> <mo>&OverBar;</mo> </mover> </mrow> <mo>|</mo> <msub> <mi>A</mi> <mi>i</mi> </msub> <mo>)</mo> </mrow> <mo>/</mo> <msub> <mi>A</mi> <mn>0</mn> </msub> <mover> <mrow> <mi>M</mi> <mi>a</mi> </mrow> <mo>&OverBar;</mo> </mover> </mrow>
<mrow> <mover> <mrow> <mi>M</mi> <mi>a</mi> </mrow> <mo>&OverBar;</mo> </mover> <mo>=</mo> <mrow> <mo>(</mo> <munderover> <mi>&Sigma;</mi> <mrow> <mi>i</mi> <mo>=</mo> <mn>1</mn> </mrow> <mi>N</mi> </munderover> <msub> <mi>Ma</mi> <mi>i</mi> </msub> <msub> <mover> <mi>m</mi> <mo>&CenterDot;</mo> </mover> <mi>i</mi> </msub> <mo>)</mo> </mrow> <mo>/</mo> <mover> <mi>m</mi> <mo>&CenterDot;</mo> </mover> </mrow>
wherein,-mass average mach number; mai-mach number at each measurement point; a. thei-the area of each measurement point;-mass flow at each measurement point; a. the0-measuring the total area of the cross section;-measuring the total mass flow of the cross section; n-dividing the measuring section into N small areas.
4. The design method of the direct connection test device for simulating the distortion flow field of the internal turning air inlet channel-circular isolation section as claimed in claim 2, is characterized in that: the flow field distortion parameter is a flow field distortion index D, and the total mass flow is represented by a dimensionless method:
<mrow> <mi>D</mi> <mo>=</mo> <mrow> <mo>(</mo> <munderover> <mo>&Sigma;</mo> <mrow> <mi>i</mi> <mo>=</mo> <mn>1</mn> </mrow> <mi>N</mi> </munderover> <mo>|</mo> <mrow> <msub> <mi>&rho;</mi> <mi>i</mi> </msub> <msub> <mi>u</mi> <mi>i</mi> </msub> <mo>-</mo> <mover> <mrow> <mi>&rho;</mi> <mi>u</mi> </mrow> <mo>&OverBar;</mo> </mover> </mrow> <mo>|</mo> <msub> <mi>A</mi> <mi>i</mi> </msub> <mo>)</mo> </mrow> <mo>/</mo> <mover> <mi>m</mi> <mo>&CenterDot;</mo> </mover> </mrow>
<mrow> <mover> <mrow> <mi>&rho;</mi> <mi>u</mi> </mrow> <mo>&OverBar;</mo> </mover> <mo>=</mo> <mrow> <mo>(</mo> <munderover> <mo>&Sigma;</mo> <mrow> <mi>i</mi> <mo>=</mo> <mn>1</mn> </mrow> <mi>N</mi> </munderover> <msub> <mi>&rho;</mi> <mi>i</mi> </msub> <msub> <mi>u</mi> <mi>i</mi> </msub> <msub> <mover> <mi>m</mi> <mo>&CenterDot;</mo> </mover> <mi>i</mi> </msub> <mo>)</mo> </mrow> <mo>/</mo> <mover> <mi>m</mi> <mo>&CenterDot;</mo> </mover> </mrow>
wherein ρ -total fluid density of the measurement cross section; u-main flow direction velocity of the measurement section, piDensity of fluid at each measurement point, ui-the speed of the main flow direction at each measuring point,for the mass flow of the respective measuring points, Ai-the area of each measurement point;to measure the total mass flow of the cross section.
5. The design method of the direct connection test device for simulating the distortion flow field of the internal turning air inlet channel-circular isolation section according to claim 1 is characterized in that: in the step (2), a specific design method of the distortion generator shape surface design is as follows:
1) obtaining a target flow field, namely the characteristics of a target air inlet under a typical working condition, including a flow field structure, parameter distribution and overall performance;
2) extracting parameters of a throat section (6) of an air inlet of a target flow field;
3) designing a distortion generation shape line;
4) adjusting parameters of an inlet flow field of the distortion generator (3), wherein the parameters comprise mass average Mach number, flow field distortion index and Mach number distortion index; determining the length of a boundary layer development section (2) according to the boundary layer thickness of the circular isolation section inlet, and adjusting the outlet Mach number of a spray pipe (1) on the basis of determining the boundary layer development section to enable the errors of inlet flow field parameters of a distortion generator (3) and inlet channel throat section (6) parameters of a target flow field to be within an allowable range, namely within 6 percent of error;
5) and selecting the total airflow deflection angle from the boundary layer development section (2) to the circular isolation section (4) according to the geometric configuration of the inward turning air inlet channel (7) of the target flow field.
6. The design method of the direct connection test device for simulating the distortion flow field of the internal turning air inlet channel-circular isolation section according to claim 1 is characterized in that: in the step (4), the inlet parameters of the boundary layer development section (2) comprise mass average Mach number, flow field distortion index, Mach number distortion index, static pressure and temperature.
7. The design method of the direct connection test device for simulating the distortion flow field of the internal turning air inlet channel-circular isolation section according to claim 1 is characterized in that: in the step (4), the spray pipe (1) with the proper surface is selected according to the inlet parameters and the flow relation of the boundary layer development section (2), and the outlet parameters of the spray pipe (1) comprise outlet Mach number, outlet area, static pressure, total pressure and temperature.
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