CN117740311A - Airflow regulating and controlling device and method for continuous supersonic wind tunnel - Google Patents
Airflow regulating and controlling device and method for continuous supersonic wind tunnel Download PDFInfo
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Abstract
The invention discloses an airflow regulating device and method for a continuous supersonic wind tunnel, which relate to the field of wind tunnels and comprise the following steps: the device comprises a first axial flow compressor, a second axial flow compressor, an outer duct, a clutch and a duct switching mechanism; the main shafts of the 2 axial flow compressors are meshed or separated through the clutch, the duct switching mechanism is used for communicating the first flow channel with the outer duct when the main shafts of the 2 axial flow compressors are separated, the communication of the first flow channel and the second flow channel is disconnected, the air flow processed by the first axial flow compressor flows into the wind tunnel main circuit after passing through the outer duct, or the duct switching mechanism is used for disconnecting the communication of the first flow channel and the outer duct when the main shafts of the 2 axial flow compressors are meshed, the first flow channel is communicated with the second flow channel, and the air flow processed by the first axial flow compressor and the air flow processed by the second axial flow compressor flows into the wind tunnel main circuit.
Description
Technical Field
The invention relates to the technical field of wind tunnel overall design, in particular to an airflow regulating device and method for a continuous supersonic wind tunnel.
Background
High speed is one of the important trends in aircraft development. The continuous supersonic wind tunnel is a core ground test platform for supporting the development of a high-speed aircraft. The continuous supersonic wind tunnel design construction is one of the extremely important core tasks in future wind tunnel design construction.
The load characteristic of the continuous supersonic wind tunnel axial flow compressor system is in an ultra-wide total pressure ratio range and an ultra-narrow flow range characteristic under the influence that the wind tunnel loop airflow loss in the supersonic speed domain increases geometrically and nonlinearly along with the Mach number. The axial flow compressor has the advantages that the axial flow compressor is influenced by the limited air inlet angle range in which the compressor blades can stably operate, and the total pressure ratio range which can be stably covered by the single-shaft axial flow compressor in the extremely narrow flow range is limited, so that the traditional single-shaft axial flow compressor layout type cannot meet the wide working condition operation requirement of the continuous supersonic wind tunnel, and development of the axial flow compressor layout type applicable to the continuous supersonic wind tunnel is urgently required.
Disclosure of Invention
In order to solve the problem that the layout type of the traditional single-shaft axial flow compressor cannot meet the operation requirement of the continuous supersonic wind tunnel under the wide working condition, the invention provides an airflow regulating device which can be used for the continuous supersonic wind tunnel, and the airflow regulating device comprises:
the device comprises a first axial flow compressor, a second axial flow compressor, an outer duct, a clutch and a duct switching mechanism; the main shaft of the first axial flow compressor is meshed with or separated from the main shaft of the second axial flow compressor through a clutch, a first flow channel is arranged between the inner shell of the first axial flow compressor and the outer shell of the first axial flow compressor, and a second flow channel is arranged between the inner shell of the second axial flow compressor and the outer shell of the second axial flow compressor; the bypass switching mechanism is used for communicating the first flow channel with the outer bypass when the main shaft of the first axial flow compressor is separated from the main shaft of the second axial flow compressor, disconnecting the communication between the first flow channel and the second flow channel, and enabling the air flow processed by the first axial flow compressor to flow into the wind tunnel main circuit after passing through the outer bypass, or disconnecting the communication between the first flow channel and the outer bypass when the main shaft of the first axial flow compressor is meshed with the main shaft of the second axial flow compressor, communicating the first flow channel with the second flow channel, and enabling the air flow processed by the first axial flow compressor and the air flow processed by the second axial flow compressor to flow into the wind tunnel main circuit.
The principle of the device is that 2 axial flow compressors are arranged in the device and can be independently operated or jointly operated, when the axial flow compressors are independently operated, the extremely narrow flow range characteristic can be obtained, when the two axial flow compressors are jointly operated, the ultra-wide total pressure ratio range can be obtained, and further, the continuous supersonic wind tunnel wide working condition operation requirement is met, and whether the two axial flow compressors are independently operated or jointly operated is realized through the cooperation of an outer duct, a clutch and a duct switching mechanism, specifically: the device is provided with the outer duct, when the first axial flow compressor is required to independently operate, the first flow channel is communicated with the outer duct, the first flow channel is disconnected from the second flow channel, the air flow processed by the first axial flow compressor flows into a wind tunnel main loop after passing through the outer duct, the operation of a single axial flow compressor is realized, when the combined operation is required, the communication between the first flow channel and the outer duct is disconnected, the first flow channel is communicated with the second flow channel, the air flow processed by the first axial flow compressor and the air flow processed by the second axial flow compressor flows into the wind tunnel main loop, the combined operation of 2 axial flow compressors is realized, the device realizes the independent and combined operation switching of the first axial flow compressor and the second axial flow compressor, and realizes the adjustment of the air flow of the wind tunnel main loop, so that the load characteristic of the continuous speed wind tunnel main compressor presents the characteristics of ultra-wide total pressure ratio range and ultra-narrow flow range, and the continuous ultrasonic speed wide working condition operation requirement can be met.
Wherein, in some embodiments, the bypass switching mechanism comprises: the device comprises a first cylinder, a first driving mechanism, a second cylinder, a second driving mechanism, a first closed cover, a third driving mechanism, a second closed cover and a fourth driving mechanism;
the first driving mechanism is used for driving the first cylinder to move forward to the inlet of the outer duct along the air flow direction of the first flow channel from the first initial position, disconnecting the outer duct from the first flow channel, and driving the first cylinder to move reversely to the first initial position along the air flow direction of the first flow channel, so that the outer duct is communicated with the first flow channel;
the second driving mechanism is used for driving the second cylinder to reversely move to the outlet of the outer duct along the air flow direction of the wind tunnel main circuit from the second initial position, disconnecting the outer duct from the wind tunnel main circuit, and driving the second cylinder to positively move to the second initial position along the air flow direction of the wind tunnel main circuit, and communicating the outer duct with the wind tunnel main circuit;
the third driving mechanism is used for driving the first closed cover to open so as to communicate the first flow channel with the second flow channel and driving the first closed cover to close so as to disconnect the first flow channel from the second flow channel;
the fourth driving mechanism is used for driving the second closed cover to open so as to communicate the second flow channel with the wind tunnel main loop, and is used for driving the second closed cover to close so as to disconnect the second flow channel from the wind tunnel main loop.
The principle of the bypass switching mechanism in the invention is as follows: when the first axial flow compressor is required to independently operate, the first flow channel is required to be communicated with the outer duct, and the communication between the first flow channel and the second flow channel is disconnected; when the first axial flow compressor and the second axial flow compressor are required to operate in a combined mode, the first closed cover and the second closed cover are opened, then the first cylinder is moved to the outer duct inlet from the first initial position, the outer duct inlet is sealed by the first cylinder, the outer duct is disconnected from the first flow channel, the second cylinder is moved to the outer duct outlet from the second initial position, the outer duct outlet is sealed by the second cylinder, the outer duct is disconnected from the second flow channel, the first flow channel and the second flow channel are finally enabled to circulate, the air flow flows into the wind tunnel main loop after being processed by the first axial flow compressor and the second axial flow compressor, and the sealing effect of the air flow is good due to the sealing effect of the first closed cover, the second closed cover, the first cylinder and the second cylinder.
Wherein, in some embodiments, the first driving mechanism is used for driving the first cylinder to move forward from the first initial position to the inlet of the outer duct along the air flow direction of the first flow channel after the first closed cover is opened, so as to disconnect the outer duct from the first flow channel;
the second driving mechanism is used for driving the second cylinder to reversely move to the outlet of the outer duct along the airflow direction of the wind tunnel main loop from the second initial position after the second closed cover is opened, and disconnecting the outer duct from being communicated with the wind tunnel main loop;
the third driving mechanism is used for driving the first closed cover to be closed after the first cylinder moves to the first initial position;
the third driving mechanism is used for driving the second airtight cover to be closed after the second cylinder moves to the second initial position.
The first cylinder needs to be moved after the first closed cover is opened, otherwise the first closed cover can block the first cylinder, so that the sealing effect is poor, similarly, the second cylinder needs to be moved after the second closed cover is opened, otherwise the second closed cover can block the second cylinder, it can be understood that the first closed cover needs to be closed after the first cylinder returns to the initial position, otherwise the first closed cover cannot be closed, and similarly, the second closed cover needs to be closed after the second cylinder returns to the initial position, otherwise the second closed cover cannot be closed.
In some embodiments, the first closed cover and the second closed cover have the same structure and comprise a plurality of arc plates, wherein the rear ends of the arc plates in the first closed cover are connected with the front edge of the outer casing of the second axial flow compressor through hinges, and the rear ends of the arc plates in the second closed cover are connected with the rear edge of the outer casing of the second axial flow compressor through hinges; after the first closed cover is closed, the front ends of the arc plates in the first closed cover are attached to the outer wall of the inner casing of the second axial flow compressor, and the side walls of the adjacent 2 arc plates in the first closed cover are attached; after the second airtight cover is closed, the front ends of the arc plates in the second airtight cover are attached to the outer wall of the inner casing of the second axial flow compressor, and the side walls of the adjacent 2 arc plates in the second airtight cover are attached.
When the first airtight cover and the second airtight cover are closed, the front ends of the arc plates are attached to the outer wall of the inner casing of the second axial flow compressor, the side walls of the adjacent 2 arc plates are attached, and therefore the purpose of design is that gaps are not reserved between the arc plates and between the inner casing and the outer wall of the second axial flow compressor, good sealing effect is guaranteed.
Wherein in some embodiments, the arcuate shape of the arcuate plate front end matches the shape of the inner housing outer wall of the second axial flow compressor, and the arcuate shape of the arcuate plate rear end matches the shape of the outer housing outer wall of the second axial flow compressor. The design is shape matching purpose and is formed good laminating, guarantee sealed effect, forms the side after a plurality of arc concatenations together and seals, both ends open-ended structure, the one end opening size of this structure matches with the interior casing outer wall size of second axial flow compressor, and the opening size of the other end matches with the outer casing outer wall size of second axial flow compressor, can carry out good sealedly to the runner between second axial flow compressor outer casing and the interior casing.
The invention also provides an air flow regulating and controlling method based on the air flow regulating and controlling device which can be used for the continuous supersonic wind tunnel, and the method comprises the following steps:
step 1: obtaining the data of the operating Mach number range of the wind tunnel and the overall size data of the wind tunnel;
step 2: calculating to obtain pressure ratio range data and flow range data corresponding to the full-working-condition operation of the wind tunnel based on the operation Mach number range data and the overall size data of the wind tunnel;
step 3: based on the pressure ratio range data and the flow range data, determining the number of the axial flow compressors corresponding to the full working condition of the covered wind tunnel and the Mach number range corresponding to the participation operation working condition of each axial flow compressor;
step 4: during wind tunnel operation, based on the number of axial compressors and Mach number range obtained in the step 3, the bypass switching mechanism is operated so that the first axial compressor operates alone or in series with the second axial compressor.
According to the method, firstly, operation Mach number range data of a wind tunnel and integral size data of the wind tunnel are obtained, then pressure ratio range data and flow range data corresponding to all-condition operation of the wind tunnel are obtained through calculation based on the data, then the number of axial flow compressors corresponding to all-condition operation of the wind tunnel and Mach number ranges corresponding to the operation conditions of all axial flow compressors are determined according to the pressure ratio range data and the flow range data, and when the wind tunnel is operated, a duct switching mechanism is operated according to the obtained number of axial flow compressors and the Mach number ranges, so that the first axial flow compressor is operated independently or is operated in series with the second axial flow compressor, and airflow parameters meeting the operation requirements of the continuous supersonic wind tunnel under wide condition can be obtained.
Wherein, in some embodiments, when the Mach number range is greater than Ma Lower limit of And is smaller than Ma Demarcation When the first axial flow compressor is only required to run, the main shaft of the first axial flow compressor is separated from the main shaft of the second axial flow compressor through the clutch, the first flow channel is communicated with the outer duct, the communication between the first flow channel and the second flow channel is disconnected, and air flow is injected into the wind tunnel main loop after passing through the first axial flow compressor and the outer duct;
when Mach number is greater than Ma Demarcation And is smaller than Ma Upper limit of When the first axial flow compressor and the second axial flow compressor are required to operate in a combined mode, the main shaft of the first axial flow compressor is meshed with the main shaft of the second axial flow compressor through the clutch, the first flow channel is disconnected from the outer culvert, the first flow channel is communicated with the second flow channel, and air flow is injected into the wind tunnel main loop after passing through the first axial flow compressor and the first axial flow compressor;
wherein the first axial flow compressor has an operating Mach number range greater than Ma Lower limit of Less than Ma Upper limit of The second axial compressor operates with a Mach number in a range greater than Ma Demarcation Less than Ma Upper limit of 。
In some embodiments, the pressure ratio corresponding to the full-working-condition operation of the wind tunnel is calculated by the following steps:
；
；
；
wherein,for the corresponding pressure ratio of the wind tunnel full working condition operation, +.>Is the average total pressure of the air flow at the outlet section of the axial flow compressor,for the average total pressure of the air flow at the inlet section of the axial flow compressor, < >>For the total pressure loss of the ith section of the wind tunnel path, < + >>For the air flow density>For the test section inlet air flow speed,/-)>Equivalent pressure loss coefficient of the ith section of the wind tunnel.
In some embodiments, the flow corresponding to the full-working-condition operation of the wind tunnel is calculated by the following steps:
；
wherein,for the corresponding flow of the wind tunnel full working condition operation, +.>For stabilizing total pressure of the segment->For stabilizing total temperature of section, +.>Is the throat area or the nozzle outlet area.
The one or more technical schemes provided by the invention have at least the following technical effects or advantages:
according to the invention, 2 axial flow compressors can be independently operated or can be jointly operated, the characteristic of extremely narrow flow range can be obtained when the axial flow compressors are independently operated, and the ultra-wide total pressure ratio range can be obtained when the two axial flow compressors are jointly operated, so that the wide working condition operation requirement of the continuous supersonic wind tunnel is met.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention;
FIG. 1 is a schematic view of a first axial compressor operating alone;
FIG. 2 is a schematic structural view of a first axial compressor operating in conjunction with a second axial compressor;
FIG. 3 is a schematic flow diagram of a method of regulating airflow;
the device comprises a first axial compressor, a second axial compressor, a 3-outer duct, a 4-first closed cover, a 5-first cylinder, a 6-second cylinder, a 7-clutch, an 8-first driving mechanism, a 9-wind tunnel main loop, a 10-second closed cover, an 11-third driving mechanism and a 12-fourth driving mechanism.
Detailed Description
In order that the above-recited objects, features and advantages of the present invention will be more clearly understood, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description. In addition, the embodiments of the present invention and the features in the embodiments may be combined with each other without collision.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced in other ways than within the scope of the description, and the scope of the invention is therefore not limited to the specific embodiments disclosed below.
Embodiment one;
referring to fig. 1-2, fig. 1 is a schematic structural diagram of a first axial compressor running alone, and fig. 2 is a schematic structural diagram of a first axial compressor running in combination with a second axial compressor, the invention provides an airflow regulating device for a continuous supersonic wind tunnel, which is characterized in that the airflow regulating device comprises:
a first axial flow compressor 1, a second axial flow compressor 2, an outer duct 3, a clutch 7 and a duct switching mechanism; the main shaft of the first axial flow compressor is meshed with or separated from the main shaft of the second axial flow compressor through a clutch, a first flow channel is arranged between the inner shell of the first axial flow compressor and the outer shell of the first axial flow compressor, and a second flow channel is arranged between the inner shell of the second axial flow compressor and the outer shell of the second axial flow compressor; the bypass switching mechanism is used for communicating the first flow channel with the outer bypass when the main shaft of the first axial flow compressor is separated from the main shaft of the second axial flow compressor, disconnecting the communication between the first flow channel and the second flow channel, and enabling the air flow processed by the first axial flow compressor to flow into the wind tunnel main circuit 9 after passing through the outer bypass, or disconnecting the communication between the first flow channel and the outer bypass when the main shaft of the first axial flow compressor is meshed with the main shaft of the second axial flow compressor, communicating the first flow channel with the second flow channel, and enabling the air flow processed by the first axial flow compressor and the air flow processed by the second axial flow compressor to flow into the wind tunnel main circuit 9.
Wherein the arrow direction in fig. 1 is the air flow direction.
The device solves the problem that the traditional single-shaft axial flow compressor cannot meet the operation requirement of the continuous supersonic wind tunnel under the wide working condition, improves the running economy and stability of the wind tunnel, and can select an operation mode which is most matched with different operation requirements of the wind tunnel according to different operation requirements of the wind tunnel.
The operation parameters of the first axial flow compressor and the second axial flow compressor in the embodiment of the invention can be adjusted according to actual needs, and the first axial flow compressor is in full working condition range to participate in operation under normal conditions, and part of working conditions of the second axial flow compressor and the first axial flow compressor are in series operation.
In an embodiment of the present invention, the bypass switching mechanism includes: a first cylinder 5, a first driving mechanism 8, a second cylinder 6, a second driving mechanism 13, a first airtight enclosure 4, a third driving mechanism 11, a second airtight enclosure 10, and a fourth driving mechanism 12;
the first driving mechanism is used for driving the first cylinder to move forward to the inlet of the outer duct along the air flow direction of the first flow channel from the first initial position, disconnecting the outer duct from the first flow channel, and driving the first cylinder to move reversely to the first initial position along the air flow direction of the first flow channel, so that the outer duct is communicated with the first flow channel;
the second driving mechanism is used for driving the second cylinder to reversely move to the outlet of the outer duct along the air flow direction of the wind tunnel main circuit from the second initial position, disconnecting the outer duct from the wind tunnel main circuit, and driving the second cylinder to positively move to the second initial position along the air flow direction of the wind tunnel main circuit, and communicating the outer duct with the wind tunnel main circuit;
the third driving mechanism is used for driving the first closed cover to open so as to communicate the first flow channel with the second flow channel and driving the first closed cover to close so as to disconnect the first flow channel from the second flow channel;
the fourth driving mechanism is used for driving the second closed cover to open so as to communicate the second flow channel with the wind tunnel main loop, and is used for driving the second closed cover to close so as to disconnect the second flow channel from the wind tunnel main loop.
The length of the first cylinder needs to be greater than the width of the outer duct inlet, and the length of the second cylinder needs to be greater than the width of the outer duct outlet, so that good sealing can be performed, and in order to have a better sealing effect, sealant, sealing strips or the like can be added to the corresponding positions of the first cylinder and the second cylinder according to requirements.
The first to fourth driving mechanisms may include hydraulic cylinders and link mechanisms, or may be other driving mechanisms, and the present invention is not limited specifically, and when the first to fourth driving mechanisms are hydraulic cylinders and link mechanisms, the hydraulic cylinders drive the link mechanisms to move, and the corresponding cylinders of the link mechanisms move and the enclosure is opened and closed. The connecting rods in the connecting rod mechanism are connected by adopting ball bearings, the hydraulic cylinder and the connecting rod mechanism jointly act to drive the closed cover to open or close, and the first cylinder and the second cylinder can be directly driven by the hydraulic cylinder.
In the embodiment of the invention, after the first closed cover is opened, the first driving mechanism is used for driving the first cylinder to move forward from the first initial position to the inlet of the outer duct along the airflow direction of the first flow channel, so that the outer duct and the first flow channel are disconnected;
the second driving mechanism is used for driving the second cylinder to reversely move to the outlet of the outer duct along the airflow direction of the wind tunnel main loop from the second initial position after the second closed cover is opened, and disconnecting the outer duct from being communicated with the wind tunnel main loop;
the third driving mechanism is used for driving the first closed cover to be closed after the first cylinder moves to the first initial position;
the third driving mechanism is used for driving the second airtight cover to be closed after the second cylinder moves to the second initial position.
In the embodiment of the invention, the first closed cover and the second closed cover have the same structure and comprise a plurality of arc plates, wherein the rear ends of the arc plates in the first closed cover are connected with the front edge of the outer casing of the second axial flow compressor through hinges, and the rear ends of the arc plates in the second closed cover are connected with the rear edge of the outer casing of the second axial flow compressor through hinges; after the first closed cover is closed, the front ends of the arc plates in the first closed cover are attached to the outer wall of the inner casing of the second axial flow compressor, and the side walls of the adjacent 2 arc plates in the first closed cover are attached; after the second airtight cover is closed, the front ends of the arc plates in the second airtight cover are attached to the outer wall of the inner casing of the second axial flow compressor, and the side walls of the adjacent 2 arc plates in the second airtight cover are attached.
Wherein, for guaranteeing sealed effect arc edge can set up the sealing strip.
The first cylinder and the second cylinder are used for controlling the outer duct to open and close, and do linear reciprocating motion, the limiting positions of the opening and closing of the first cylinder are left limiting and right limiting respectively, the limiting positions of the opening and closing of the second cylinder are right limiting and left limiting respectively, and the stroke sizes of the first cylinder and the second cylinder are related to the closing included angle of the arc-shaped plate and the inner diameter and the outer diameter of the first axial flow compressor. When the outer duct is opened, the first closed cover and the second closed cover are closed, and the first cylinder and the second cylinder run to a left limit position and a right limit position respectively (as shown in figure 1); when the outer duct is closed, the first and second closure caps open and the first and second cylinders operate to the right and left extreme positions, respectively (see fig. 2).
In the embodiment of the invention, the arc shape of the front end of the arc-shaped plate is matched with the shape of the outer wall of the inner casing of the second axial flow compressor, and the arc shape of the rear end of the arc-shaped plate is matched with the shape of the outer wall of the outer casing of the second axial flow compressor.
Wherein, the outer duct is a circular airflow channel. In order to balance the diffusion loss and friction loss of the air flow, the ratio of the outer duct area to the flow area of the first axial flow compressor is 0.9-1.1; in order to control the air flow separation and further reduce loss and improve the quality of a flow field, the outer duct pneumatic molded line at least meets the second-order continuity.
The outer duct is controlled to open and close by the arc-shaped plate, the arc-shaped plate is connected with the front and rear edges of the inner shell of the second axial flow compressor by the hinge and is connected with the hydraulic cylinder by the connecting rod mechanism, and the outer duct is opened or closed under the action of the hydraulic cylinder and the connecting rod structure. In order to ensure that the first cylinder and the second cylinder move axially smoothly, the included angle between the arc plate and the horizontal axis of the second axial flow compressor is 0-5.0 degrees when the first cylinder and the second cylinder are opened, and in order to reduce the loss generated when the airflow deflects, the included angle between the arc plate and the horizontal axis of the second axial flow compressor is 15-35 degrees when the first cylinder and the second cylinder are closed, and the integrated consideration of reducing the flow loss, improving the quality of a flow field and reducing the size of a layout space is realized.
The clutch is arranged between the first axial flow compressor and the second axial flow compressor and used for controlling the engagement and disengagement of the main shafts of the first axial flow compressor and the second axial flow compressor, the clutch mode of the ducted axial flow compressor system is stop clutch, the clutch type is overrun clutch, and the clutch safety coefficient is not less than 1.5.
Embodiment two;
on the basis of the embodiment, a second embodiment of the present invention provides an airflow adjusting and controlling method based on the airflow adjusting and controlling device that can be used for a continuous supersonic wind tunnel, please refer to fig. 3, fig. 3 is a flow chart diagram of the airflow adjusting and controlling method, and the method includes:
step 1: obtaining the data of the operating Mach number range of the wind tunnel and the overall size data of the wind tunnel;
step 2: calculating to obtain pressure ratio range data and flow range data corresponding to the full-working-condition operation of the wind tunnel based on the operation Mach number range data and the overall size data of the wind tunnel;
step 3: based on the pressure ratio range data and the flow range data, determining the number of the axial flow compressors corresponding to the full working condition of the covered wind tunnel and the Mach number range corresponding to the participation operation working condition of each axial flow compressor;
step 4: during wind tunnel operation, based on the number of axial compressors and Mach number range obtained in the step 3, the bypass switching mechanism is operated so that the first axial compressor operates alone or in series with the second axial compressor.
In the embodiment of the invention, when the Mach number range is greater than Ma Lower limit of And is smaller than Ma Demarcation When the air flow is in use, the main shaft of the first axial flow compressor is separated from the main shaft of the second axial flow compressor through the clutch, the first flow channel is communicated with the outer duct, the communication between the first flow channel and the second flow channel is disconnected, and air flow is injected into the wind tunnel main loop after passing through the first axial flow compressor and the outer duct;
when Mach number is greater than Ma Demarcation And is smaller than Ma Upper limit of When the wind tunnel main loop is in use, the main shaft of the first axial flow compressor is meshed with the main shaft of the second axial flow compressor through the clutch, the first flow channel is disconnected from the outer duct, the first flow channel is communicated with the second flow channel, and air flows are injected into the wind tunnel main loop after passing through the first axial flow compressor and the first axial flow compressor;
wherein the first axial flow compressor has an operating Mach number range greater than Ma Lower limit of Less than Ma Upper limit of The second axial compressor operates with a Mach number in a range greater than Ma Demarcation Less than Ma Upper limit of 。
In the embodiment of the invention, the calculation mode of the pressure ratio corresponding to the full-working-condition operation of the wind tunnel is as follows:
；
；
；
wherein,for the corresponding pressure ratio of the wind tunnel full working condition operation, +.>Is the average total pressure of the air flow at the outlet section of the axial flow compressor,for the average total pressure of the air flow at the inlet section of the axial flow compressor, < >>For the total pressure loss of the ith section of the wind tunnel path, < + >>For the air flow density>For the test section inlet air flow speed,/-)>Equivalent pressure loss coefficient of the ith section of the wind tunnel.
In the embodiment of the invention, the flow corresponding to the full-working-condition operation of the wind tunnel is calculated by the following steps:
；
wherein,for the corresponding flow of the wind tunnel full working condition operation, +.>For stabilizing total pressure of the segment->For stabilizing total temperature of section, +.>Is the throat area or the nozzle outlet area.
And step 2, determining the number of compressors which are required to be connected in series and the Mach number range corresponding to the participation operation working condition of each compressor according to the pressure ratio and the flow range determined in the step 1. The number of compressors required for the continuous supersonic wind tunnel is generally greater than or equal to 2. Assuming a required number of 2 and assuming an operating Mach number demarcation point of Ma Demarcation The first axial compressor and the second axial compressor are operatedThe Mach number ranges of the rows are (Ma Lower limit of ，Ma Upper limit of ) Sum (Ma) Demarcation ，Ma Upper limit of ）；
The outer side of the second axial flow compressor runner (inner duct) is parallelly provided with an annular outer duct, and a duct switching mechanism consisting of a closed cover, a cylinder and a channel mechanism is respectively arranged at the inlet of the second axial flow compressor and the outer duct, and at the outlet of the second axial flow compressor and the outer duct.
When the wind tunnel runs, the bypass switching mechanism is operated according to the Mach number range limit determined in the step 2, so that the first axial flow compressor independently runs or the first axial flow compressor and the second axial flow compressor run in series, and the specific flow is as follows;
when Mach number of wind tunnel test section is (Ma Lower limit of ，Ma Demarcation ) When the clutch is disengaged, the inlet and outlet duct switching mechanism is closed (the closed cover plate is closed, the first cylinder moves to the left limit, the second cylinder moves to the right limit), and air flow is injected into the wind tunnel main loop after passing through the first axial flow compressor and the outer duct (see figure 1);
when the Mach number required by the wind tunnel test section is (Ma Demarcation ，Ma Upper limit of ) When the range is reached, the clutch is engaged, the inlet and outlet duct switching mechanisms are opened (the closed cover is opened, the first cylinder moves to the right limit, the second cylinder moves to the left limit), and air flow is injected into the wind tunnel main loop through the first axial flow compressor and the second axial flow compressor (see figure 2).
The following examples are presented:
the Mach number of the operation of a certain continuous supersonic wind tunnel is Ma1.5-Ma3.0. The air flow in the wind tunnel is driven by 2 axial flow compressors. The Mach number range of the first axial flow compressor participating in operation is Ma1.5-Ma3.0, and the Mach number range of the second axial flow compressor participating in operation is Ma2.5-Ma3.0.
The outer side of the first axial flow compressor is provided with an outer duct in parallel, and the ratio of the flow area of the outer duct to the area of the first axial flow compressor is 1.0; the inlet and outlet of the outer duct are provided with a duct switching mechanism consisting of a turning plate, a guide cylinder and an executing mechanism. The included angles between the turning plate and the axis of the compressor when the turning plate is opened and closed are 0.0 DEG and 20 deg respectively. The turning plate is connected with the hydraulic cylinder through a connecting rod structure and is used for controlling the turning plate to open and close around the hinge. The guide cylinder is connected with the hydraulic cylinder, and is controlled to move along the axial direction of the compressor, and the maximum axial displacement of the guide cylinder is 250mm. A clutch is adopted between the first axial flow compressor and the second axial flow compressor, and the safety coefficient of the clutch is 1.5.
The running flow of a certain continuous supersonic wind tunnel is as follows:
when the Mach number range of the wind tunnel test section is Ma1.5-Ma2.5, the clutch is disconnected, and the first axial flow compressor independently operates. At the moment, the first cylinder of the inlet duct switching mechanism moves to the left limit under the action of the electric actuator, and the first closed cover is closed; the second cylinder moves to the right limit, and the second closed cover is closed; at this time, the outer duct is in an open state, and the air flow of the wind tunnel loop is reinjected into the wind tunnel loop through the first axial flow compressor and the outer duct;
when the Mach number range of the wind tunnel test section is Ma2.5-Ma3.0, the clutch is engaged, and the first axial flow compressor and the second axial flow compressor are operated in series. At this time, the first closed cover is opened, and the first cylinder moves to the right limit; the second closed cover is completely opened, and the second cylinder moves to the left limit; the outer duct is in a closed state, and the wind tunnel loop airflow is re-injected into the wind tunnel loop through the first axial flow compressor and the second axial flow compressor.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following claims be interpreted as including the preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (9)
1. An air flow regulating device for a continuous supersonic wind tunnel, comprising:
the device comprises a first axial flow compressor, a second axial flow compressor, an outer duct, a clutch and a duct switching mechanism; the main shaft of the first axial flow compressor is meshed with or separated from the main shaft of the second axial flow compressor through a clutch, a first flow channel is arranged between the inner shell of the first axial flow compressor and the outer shell of the first axial flow compressor, and a second flow channel is arranged between the inner shell of the second axial flow compressor and the outer shell of the second axial flow compressor; the bypass switching mechanism is used for communicating the first flow channel with the outer bypass when the main shaft of the first axial flow compressor is separated from the main shaft of the second axial flow compressor, disconnecting the communication between the first flow channel and the second flow channel, and enabling the air flow processed by the first axial flow compressor to flow into the wind tunnel main circuit after passing through the outer bypass, or disconnecting the communication between the first flow channel and the outer bypass when the main shaft of the first axial flow compressor is meshed with the main shaft of the second axial flow compressor, communicating the first flow channel with the second flow channel, and enabling the air flow processed by the first axial flow compressor and the air flow processed by the second axial flow compressor to flow into the wind tunnel main circuit.
2. The airflow control device for a continuous supersonic wind tunnel according to claim 1, wherein the bypass switching mechanism comprises: the device comprises a first cylinder, a first driving mechanism, a second cylinder, a second driving mechanism, a first closed cover, a third driving mechanism, a second closed cover and a fourth driving mechanism;
the first driving mechanism is used for driving the first cylinder to move forward to the inlet of the outer duct along the air flow direction of the first flow channel from the first initial position, disconnecting the outer duct from the first flow channel, and driving the first cylinder to move reversely to the first initial position along the air flow direction of the first flow channel, so that the outer duct is communicated with the first flow channel;
the second driving mechanism is used for driving the second cylinder to reversely move to the outlet of the outer duct along the air flow direction of the wind tunnel main circuit from the second initial position, disconnecting the outer duct from the wind tunnel main circuit, and driving the second cylinder to positively move to the second initial position along the air flow direction of the wind tunnel main circuit, and communicating the outer duct with the wind tunnel main circuit;
the third driving mechanism is used for driving the first closed cover to open so as to communicate the first flow channel with the second flow channel and driving the first closed cover to close so as to disconnect the first flow channel from the second flow channel;
the fourth driving mechanism is used for driving the second closed cover to open so as to communicate the second flow channel with the wind tunnel main loop, and is used for driving the second closed cover to close so as to disconnect the second flow channel from the wind tunnel main loop.
3. The airflow control device for the continuous supersonic wind tunnel according to claim 2, wherein the first driving mechanism is used for driving the first cylinder to move forward from the first initial position to the inlet of the outer duct along the airflow direction of the first flow channel after the first closed cover is opened, so as to disconnect the outer duct from the first flow channel;
the second driving mechanism is used for driving the second cylinder to reversely move to the outlet of the outer duct along the airflow direction of the wind tunnel main loop from the second initial position after the second closed cover is opened, and disconnecting the outer duct from being communicated with the wind tunnel main loop;
the third driving mechanism is used for driving the first closed cover to be closed after the first cylinder moves to the first initial position;
the third driving mechanism is used for driving the second airtight cover to be closed after the second cylinder moves to the second initial position.
4. The airflow control device for the continuous supersonic wind tunnel according to claim 2, wherein the first closed cover and the second closed cover have the same structure and comprise a plurality of arc plates, wherein the rear ends of the arc plates in the first closed cover are connected with the front edge of the outer shell of the second axial compressor through hinges, and the rear ends of the arc plates in the second closed cover are connected with the rear edge of the outer shell of the second axial compressor through hinges; after the first closed cover is closed, the front ends of the arc plates in the first closed cover are attached to the outer wall of the inner casing of the second axial flow compressor, and the side walls of the adjacent 2 arc plates in the first closed cover are attached; after the second airtight cover is closed, the front ends of the arc plates in the second airtight cover are attached to the outer wall of the inner casing of the second axial flow compressor, and the side walls of the adjacent 2 arc plates in the second airtight cover are attached.
5. The airflow control device for a continuous supersonic wind tunnel according to claim 4, wherein the shape of the arc of the front end of the arc plate is matched with the shape of the outer wall of the inner casing of the second axial compressor, and the shape of the arc of the rear end of the arc plate is matched with the shape of the outer wall of the outer casing of the second axial compressor.
6. An air flow regulating method based on the air flow regulating device for continuous supersonic wind tunnel according to any one of claims 1-5, characterized in that the method comprises:
step 1: obtaining the data of the operating Mach number range of the wind tunnel and the overall size data of the wind tunnel;
step 2: calculating to obtain pressure ratio range data and flow range data corresponding to the full-working-condition operation of the wind tunnel based on the operation Mach number range data and the overall size data of the wind tunnel;
step 3: based on the pressure ratio range data and the flow range data, determining the number of the axial flow compressors corresponding to the full working condition of the covered wind tunnel and the Mach number range corresponding to the participation operation working condition of each axial flow compressor;
step 4: during wind tunnel operation, based on the number of axial compressors and Mach number range obtained in the step 3, the bypass switching mechanism is operated so that the first axial compressor operates alone or in series with the second axial compressor.
7. The air flow control method according to claim 6, wherein:
when Mach number is greater than Ma Lower limit of And is smaller than Ma Demarcation When the air flow is in use, the main shaft of the first axial flow compressor is separated from the main shaft of the second axial flow compressor through the clutch, the first flow channel is communicated with the outer duct, the communication between the first flow channel and the second flow channel is disconnected, and air flow is injected into the wind tunnel main loop after passing through the first axial flow compressor and the outer duct;
when Mach number is greater than Ma Demarcation And is smaller than Ma Upper limit of When the wind tunnel main loop is in use, the main shaft of the first axial flow compressor is meshed with the main shaft of the second axial flow compressor through the clutch, the first flow channel is disconnected from the outer duct, the first flow channel is communicated with the second flow channel, and air flows are injected into the wind tunnel main loop after passing through the first axial flow compressor and the first axial flow compressor;
wherein the first axial flow compressor has an operating Mach number range greater than Ma Lower limit of Less than Ma Upper limit of The second axial compressor operates with a Mach number in a range greater than Ma Demarcation Less than Ma Upper limit of 。
8. The airflow control method according to claim 6, wherein the pressure ratio corresponding to the full-condition operation of the wind tunnel is calculated by:
；
wherein,for the corresponding pressure ratio of the wind tunnel full working condition operation, +.>For the average total pressure of the air flow at the outlet section of the axial flow compressor, < >>For the average total pressure of the air flow at the inlet section of the axial flow compressor, < >>For the total pressure loss of the ith section of the wind tunnel path, < + >>For the air flow density>For the inlet air flow velocity of the test section，/>Equivalent pressure loss coefficient of the ith section of the wind tunnel.
9. The airflow control method according to claim 6, wherein the flow corresponding to the full-condition operation of the wind tunnel is calculated by:
；
wherein,for the corresponding flow of the wind tunnel full working condition operation, +.>For stabilizing total pressure of the segment->For stabilizing total temperature of section, +.>Is the throat area or the nozzle outlet area.
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