Inlet swirl adjustment device for a test piece of a reheat combustor and design method thereof

Abstract

This invention relates to the field of aero-engine technology, and discloses an inlet swirl adjustment device and its design method for an afterburner test component. A flow divider ring is used to segment the test flow channel into an inner flow channel and an outer bypass flow channel for simulating the airflow in the inner flow channel. The remaining linkage control structures are installed in the outer bypass casing or outer bypass flow channel to reduce interference with the inner flow channel. The linkage adjustment assembly performs overall synchronous adjustment of all adjustable guide vanes, ultimately achieving adjustment of the inner airflow angle, thereby simulating the inner airflow of the afterburner and reducing testing costs and overall engine verification risks. The inlet airflow swirl adjustment device of this invention comprehensively considers the relevant requirements of total pressure recovery coefficient and airflow uniformity index, ensuring high-precision and high-stability simulation of the inner airflow of the afterburner. Furthermore, its simple structure allows for easy assembly and replacement, providing flexible support for afterburner performance testing under different operating conditions.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and discloses an inlet swirl adjustment device for an afterburner test piece and its design method. Background Technology

[0002] For aero-engines, the inlet airflow of the afterburner originates from the turbine components. Directly validating a newly developed afterburner on the engine carries significant risks; therefore, testing is typically conducted first on a test platform. Thus, ensuring the airflow conditions between the test platform and the engine turbine outlet are crucial. Conventional airflow regulation devices generally have only one flow channel, similar to an aero-engine compressor, with the corresponding regulation device directly mounted on the outer casing of the flow channel. However, turbofan afterburner prototypes contain two flow channels. The goal is to regulate the airflow in the inner flow channel while simultaneously mounting the relevant devices on the outer flow channel casing; a simple structure, easy assembly, and good sealing performance are also required to minimize leakage and cross-flow between the inner and outer flow channels. However, existing inlet regulation devices for afterburner prototypes struggle to meet these requirements, especially under complex operating conditions, exhibiting insufficient regulation accuracy and stability. Summary of the Invention

[0003] The purpose of this invention is to provide an inlet swirl adjustment device and its design method for an afterburner test piece, which can simulate the internal airflow of the afterburner, reduce test costs and overall verification risks; the inlet airflow swirl adjustable device has a simple structure, can be easily assembled and replaced, and can provide flexible support for afterburner performance testing under different operating conditions.

[0004] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:

[0005] An inlet swirl adjustment device for an afterburner test piece includes: The sector-shaped casing includes an inner ring casing and an outer ring casing arranged coaxially; Two guide vanes are radially disposed in the arc-shaped area between the inner and outer ring casings; the two guide vanes, the inner ring casing, and the outer ring casing together form the test flow channel; A flow divider ring is coaxially disposed in the arc-shaped region between the inner ring casing and the outer ring casing, and the flow divider ring divides the test flow channel into an inner flow channel and an outer flow channel; Multiple adjustable guide vanes are equidistantly installed within the inner flow channel; the lower journal of each adjustable guide vane is movably mounted on the inner ring casing, and the upper journal of each adjustable guide vane passes sequentially through the flow divider ring and the outer ring casing, and is movably mounted on the guide vane mounting seat of the outer ring casing. The linkage adjustment component is used to simultaneously drive the deflection of all adjustable guide vanes.

[0006] Furthermore, the flow divider ring is divided into a front section and a rear section along the axial direction of the fan-shaped casing. The axial division position of the front section and the rear section is located in the axial plane where the center axis of the upper journal of the adjustable guide vane is located, so as to divide the perforation of the upper journal on the flow divider ring into two semi-annular notches located on the front section and the rear section.

[0007] Furthermore, the linkage adjustment component includes: The linkage ring is coaxially mounted on the outer wall of the outer ring casing; A drive rod, installed on the outer wall of the outer ring housing, is used to drive the linkage ring to rotate circumferentially; The rocker arm has one end hinged to the linkage ring and the other end fixedly connected to the upper journal of the corresponding adjustable guide vane, and is used to drive the adjustable guide vane to rotate.

[0008] Furthermore, the inner ring casing is provided with a swivel groove at a position corresponding to the lower journal of the adjustable guide vane, which mates with the lower journal of the corresponding adjustable guide vane.

[0009] Furthermore, a limit block is also fixed on the outer ring casing, and the limit block is used to be fixedly connected to the linkage adjustment assembly by bolts.

[0010] To achieve the above-mentioned technical effects, the present invention also provides a design method for an inlet swirl adjustment device for an afterburner test specimen, used to obtain the aforementioned inlet swirl adjustment device for the afterburner test specimen, comprising: A finite element simulation model of the inlet swirl adjustment device of the afterburner test specimen, including the fan-shaped casing, guide vane, flow splitting ring, and adjustable guide vane, was constructed. Based on the internal flow channel dimensions, number of adjustable guide vanes, and adjustable guide vane dimension parameters between the two guide vanes in the finite element simulation model, the total pressure recovery coefficient and uniformity index of the internal flow channel under the test operating conditions are analyzed and obtained; the dimension parameters of the adjustable guide vanes include the blade chord length and the maximum blade thickness. Using the incoming flow conditions under the test conditions as input, the finite element simulation model is simulated and analyzed to obtain the simulated value of the total pressure recovery coefficient of the inner channel and the simulated value of the airflow uniformity at the outlet of the inner channel. If the maximum value of the simulated total pressure recovery coefficient is less than the corresponding total pressure recovery coefficient index, or the absolute value of the relative deviation between the simulated airflow uniformity value and the uniformity index is greater than a preset relative threshold, then the maximum thickness of the adjustable guide vane is adjusted until the maximum value of the simulated total pressure recovery coefficient is greater than or equal to the corresponding total pressure recovery coefficient index, and the absolute value of the relative deviation between the simulated airflow uniformity value and the uniformity index is less than or equal to the preset relative threshold. Then, the three-dimensional model of the inlet swirl adjustment device of the adjusted afterburner test piece is output.

[0011] Furthermore, the total pressure recovery coefficient index of the internal flow channel under the evaluation operating conditions is based on... Analysis yielded, among which This represents the lower limit of the total pressure recovery coefficient for the internal flow channel corresponding to the current finite element simulation model. As the first coefficient, The value range is 0 to 1. The number of adjustable guide vanes in the internal flow channel. The maximum thickness of the adjustable guide vane blade. The length of the arc in the inner flow channel between the two guide vanes. To assess the incoming Mach number under the operating conditions.

[0012] Furthermore, the uniformity index of the internal flow channel under the evaluation operating conditions is based on... Analysis yielded, among which This represents the lower limit of the uniformity of the internal flow channel corresponding to the current finite element simulation model. As the second coefficient, The value range is 1.5 to 2.5. The number of adjustable guide vanes in the internal flow channel. The chord length of the adjustable guide vane, The length of the arc in the inner flow channel between the two guide vanes.

[0013] Compared with the prior art, the beneficial effects of this invention are: 1. This invention forms a test flow channel by setting a guide vane between the inner casing and the outer casing. The test flow channel is divided into an inner flow channel and an outer flow channel by a flow splitting ring. Adjustable guide vanes are installed in the inner flow channel to simulate the airflow in the inner flow channel. The remaining linkage control structure is installed in the outer casing or outer flow channel to reduce interference with the inner flow channel. The linkage adjustment component performs overall synchronous adjustment of all adjustable guide vanes, and finally realizes the adjustment of the inner airflow angle, thereby simulating the inner airflow of the afterburner, reducing test costs and the risk of whole-engine verification.

[0014] 2. The inlet airflow swirl adjustable device of the present invention comprehensively considers the relevant requirements of total pressure recovery coefficient and airflow uniformity index, ensuring that it can achieve high-precision and high-stability simulation of the airflow inside the afterburner. Moreover, its structure is simple, which can be easily assembled and replaced, and the inlet airflow swirl can be adjusted as needed, thereby providing flexible support for afterburner performance testing under different operating conditions. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the inlet swirl adjustment device of the afterburner test specimen in the embodiment; Figure 2This is a schematic diagram showing the connection relationship between the linkage adjustment component and the adjustable guide vane in the embodiment; Figure 3 This is a schematic diagram of the segmented structure of the flow divider ring in the embodiment; Figure 4 This is a schematic diagram of the fan-shaped casing in the embodiment; Among them, 1. Inner ring casing; 101. Swirl groove; 2. Outer ring casing; 3. Guide plate; 4. Flow splitting ring; 401. Front section; 402. Rear section; 403. Notch; 5. Adjustable guide vane; 501. Lower journal; 502. Upper journal; 6. Linkage ring; 7. Rocker arm; 8. Limit block. Detailed Implementation

[0016] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0017] Example See Figures 1 to 4 An inlet swirl adjustment device for an afterburner test piece, comprising: The sector-shaped casing includes an inner ring casing 1 and an outer ring casing 2 arranged coaxially; Two guide vanes 3 are radially disposed in the arc-shaped area between the inner ring casing 1 and the outer ring casing 2; the two guide vanes 3, the inner ring casing 1, and the outer ring casing 2 together form the test flow channel; The flow divider ring 4 is coaxially disposed in the arc-shaped area between the inner ring casing 1 and the outer ring casing 2, and the flow divider ring 4 divides the test flow channel into an inner flow channel and an outer flow channel; Multiple adjustable guide vanes 5 are installed at equal intervals within the inner flow channel; the lower journal 501 of each adjustable guide vane 5 is movably mounted on the inner ring casing 1, and the upper journal 502 of each adjustable guide vane 5 passes through the flow divider ring 4 and the outer ring casing 2 in sequence, and is movably mounted on the guide vane mounting seat of the outer ring casing 2. The linkage adjustment component is used to simultaneously drive all adjustable guide vanes 5 to deflect.

[0018] In this embodiment, a guide vane 3 is set between the inner casing and the outer bypass casing to form a test flow channel. A flow splitting ring 4 is used to divide the test flow channel into an inner flow channel and an outer bypass flow channel. Adjustable guide vanes 5 are installed in the inner flow channel to simulate the airflow in the inner flow channel. The remaining linkage control structure is installed in the outer bypass casing or the outer bypass flow channel to reduce interference with the inner flow channel. The linkage adjustment component performs overall synchronous adjustment of all adjustable guide vanes 5 to ultimately adjust the inner airflow angle, thereby simulating the airflow in the afterburner and reducing test costs and overall engine verification risks. In addition, the inlet airflow swirl adjustable device in this embodiment has a simple structure and can be easily assembled and replaced.

[0019] In this embodiment, the flow divider ring 4 is divided into a front section 401 and a rear section 402 along the axial direction of the fan-shaped casing. The axial division point of the front section 401 and the rear section 402 is located in the axial plane of the central axis of the upper journal 502 of the adjustable guide vane 5, so that the perforation of the upper journal 502 on the flow divider ring 4 is divided into two semi-annular notches 403 located on the front section 401 and the rear section 402. Considering assemblability, this embodiment adopts a segmented structure for the flow divider ring 4, dividing it into a front section 401 and a rear section 402. During installation, the bushing is simultaneously fitted into the upper journal 502 of the adjustable guide vane 5, and then the front section 401 and the rear section 402 of the flow divider ring 4 are fixed inside the fan-shaped casing. The bushing and the notch 403 are used to seal the flow, reducing leakage of the two airflows in the afterburner.

[0020] The linkage adjustment component in this embodiment includes: Linkage ring 6 is coaxially mounted on the outer wall of outer ring casing 2; A drive rod is installed on the outer wall of the outer ring housing 2, and its drive end is connected to the linkage ring 6 to drive the linkage ring 6 to rotate circumferentially. The rocker arm 7 is hinged at one end to the linkage ring 6 and fixedly connected at the other end to the upper journal 502 of the corresponding adjustable guide vane 5, and is used to drive the adjustable guide vane 5 to rotate.

[0021] Each rocker arm 7 is connected to the linkage ring 6 via a precise hinge structure, ensuring stability and reliability during transmission. When the drive rod rotates the linkage ring 6, the rocker arm 7 swings accordingly, thereby transmitting power to the upper journal 502 of the adjustable guide vane 5 to achieve precise adjustment of the guide vane angle.

[0022] In this embodiment, the inner ring housing 1 is provided with a swivel groove 101 at a position corresponding to the lower journal 501 of the adjustable guide vane 5, which mates with the lower journal 501 of the adjustable guide vane 5. In this embodiment, the swivel groove 101 can be designed as an integral structure with the inner ring housing 1, and the lower journal 501 of the adjustable guide vane 5 can be directly inserted into the swivel groove 101, so that the adjustable guide vane 5 can rotate freely within the swivel groove 101.

[0023] In this embodiment, a limiting block 8 is also fixed on the outer ring casing 2. The limiting block 8 is used to fix the linkage adjustment assembly by bolts. After the adjustable guide vane 5 reaches the angle required for the test, the limiting block 8 is used to connect the linkage ring 6 to the limiting block 8 by bolts, thereby fixing the position of the linkage ring 6 and ensuring that the angle of the adjustable guide vane 5 remains stable during the test, avoiding angle deviation caused by external interference or vibration, and effectively improving the overall reliability of the device.

[0024] Based on the same inventive concept, this embodiment also provides a design method for an inlet swirl adjustment device for an afterburner test specimen, used to obtain the aforementioned inlet swirl adjustment device for the afterburner test specimen, comprising: A finite element simulation model of the inlet swirl adjustment device of the afterburner test piece, including the fan-shaped casing, guide vane 3, flow splitting ring 4, and adjustable guide vane 5, was constructed. Based on the internal flow channel dimensions between the two guide vanes 3, the number of adjustable guide vanes 5, and the size parameters of the adjustable guide vanes 5 in the finite element simulation model, the total pressure recovery coefficient and uniformity index of the internal flow channel under the test working condition are analyzed and obtained; the size parameters of the adjustable guide vanes 5 include the blade chord length and the maximum blade thickness. Using the incoming flow conditions under the test conditions as input, the finite element simulation model is simulated and analyzed to obtain the simulated value of the total pressure recovery coefficient of the inner channel and the simulated value of the airflow uniformity at the outlet of the inner channel. If the maximum value of the simulated total pressure recovery coefficient is less than the corresponding total pressure recovery coefficient index, or the absolute value of the relative deviation between the simulated airflow uniformity value and the uniformity index is greater than a preset relative threshold, then the maximum thickness of the adjustable guide vane 5 is adjusted until the maximum value of the simulated total pressure recovery coefficient is greater than or equal to the corresponding total pressure recovery coefficient index, and the absolute value of the relative deviation between the simulated airflow uniformity value and the uniformity index is less than or equal to a preset relative threshold. Then, the adjusted three-dimensional model of the inlet swirl adjustment device of the afterburner test piece is output.

[0025] In this embodiment, the structural design of the inlet swirl adjustment device for the afterburner test piece comprehensively considers the relevant requirements of the total pressure recovery coefficient and airflow uniformity index. By using finite element simulation technology in combination with specific operating conditions, the key parameters of the adjustable guide vane 5 are iteratively adjusted multiple times, thereby achieving precise control of the internal flow field characteristics of the device. This not only improves design efficiency but also significantly reduces test costs, ensuring high-precision and high-stability simulation of the internal airflow of the afterburner. Furthermore, its simple structure allows for easy assembly and replacement, and the inlet airflow swirl can be adjusted as needed, thus providing flexible support for afterburner performance testing under different operating conditions.

[0026] In this embodiment, the total pressure recovery coefficient index of the inner flow channel under the evaluation condition of incoming flow is based on... Analysis yielded, among which This represents the lower limit of the total pressure recovery coefficient for the internal flow channel corresponding to the current finite element simulation model. As the first coefficient, The value range is 0 to 1. The number of adjustable guide vanes 5 in the internal flow channel. The maximum thickness of the blade of the adjustable guide vane 5 is [missing information]. The length of the arc in the inner flow channel between the two guide vanes 3. To assess the incoming flow Mach number under evaluation conditions, the uniformity index of the internal flow channel under these conditions is based on... Analysis yielded, among which This represents the lower limit of the uniformity of the internal flow channel corresponding to the current finite element simulation model. As the first coefficient, The value range is 1.5 to 2.5. The number of adjustable guide vanes 5 in the internal flow channel. The chord length of the adjustable guide vane 5, The length of the arc in the inner flow channel between the two guide vanes 3.

[0027] This embodiment determines the total pressure recovery coefficient and uniformity index of the inner channel based on the relevant structural dimensions of the imported cosine regulating device and the incoming flow conditions. In particular, it can ensure that the total pressure recovery coefficient can be adjusted with the adjustment of the relevant structural dimensions, without relying on fixed parameter settings. It can effectively meet the performance requirements under different operating conditions, ensure that it can achieve better aerodynamic characteristics under various operating conditions, and ensure that the device can adapt to a variety of complex operating conditions, thereby improving the adaptability and flexibility of the device and meeting the requirements of its high-performance testing.

[0028] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A residual swirl adjustment device for the inlet of an afterburner test specimen, characterized in that, include: The sector-shaped casing includes an inner ring casing and an outer ring casing arranged coaxially; Two guide vanes are radially disposed in the arc-shaped area between the inner and outer ring casings; the two guide vanes, the inner ring casing, and the outer ring casing together form the test flow channel; A flow divider ring is coaxially disposed in the arc-shaped region between the inner ring casing and the outer ring casing, and the flow divider ring divides the test flow channel into an inner flow channel and an outer flow channel; Multiple adjustable guide vanes are equidistantly installed within the inner flow channel; the lower journal of each adjustable guide vane is movably mounted on the inner ring casing, and the upper journal of each adjustable guide vane passes sequentially through the flow divider ring and the outer ring casing, and is movably mounted on the guide vane mounting seat of the outer ring casing. The linkage adjustment component is used to simultaneously drive the deflection of all adjustable guide vanes.

2. The afterburner test specimen inlet swirl adjustment device according to claim 1, characterized in that, The flow divider ring is divided into a front section and a rear section along the axial direction of the fan-shaped casing. The axial division position of the front section and the rear section is located in the axial plane where the center axis of the upper journal of the adjustable guide vane is located, so as to divide the perforation of the upper journal on the flow divider ring into two semi-annular notches located on the front section and the rear section.

3. The afterburner test specimen inlet swirl adjustment device according to claim 1, characterized in that, The linkage adjustment component includes: The linkage ring is coaxially mounted on the outer wall of the outer ring casing; A drive rod, installed on the outer wall of the outer ring housing, is used to drive the linkage ring to rotate circumferentially; The rocker arm has one end hinged to the linkage ring and the other end fixedly connected to the upper journal of the corresponding adjustable guide vane, and is used to drive the adjustable guide vane to rotate.

4. The afterburner test specimen inlet swirl adjustment device according to claim 1, characterized in that, The inner ring casing has a swivel groove at a position corresponding to the lower journal of the adjustable guide vane, which mates with the lower journal of the adjustable guide vane.

5. The afterburner test specimen inlet swirl adjustment device according to claim 1, characterized in that, A limit block is also fixed on the outer ring casing, and the limit block is used to be fixedly connected to the linkage adjustment assembly by bolts.

6. A design method for an inlet swirl adjustment device for an afterburner test specimen, used to obtain the inlet swirl adjustment device for an afterburner test specimen as described in any one of claims 1-5, characterized in that, include: A finite element simulation model of the inlet swirl adjustment device of the afterburner test specimen, including the fan-shaped casing, guide vane, flow splitting ring, and adjustable guide vane, was constructed. Based on the internal flow channel dimensions, number of adjustable guide vanes, and adjustable guide vane dimension parameters between the two guide vanes in the finite element simulation model, the total pressure recovery coefficient and uniformity index of the internal flow channel under the test operating conditions are analyzed and obtained; the dimension parameters of the adjustable guide vanes include the blade chord length and the maximum blade thickness. Using the incoming flow conditions under the test conditions as input, the finite element simulation model is simulated and analyzed to obtain the simulated value of the total pressure recovery coefficient of the inner channel and the simulated value of the airflow uniformity at the outlet of the inner channel. If the maximum value of the simulated total pressure recovery coefficient is less than the corresponding total pressure recovery coefficient index, or the absolute value of the relative deviation between the simulated airflow uniformity value and the uniformity index is greater than a preset relative threshold, then the maximum thickness of the adjustable guide vane is adjusted until the maximum value of the simulated total pressure recovery coefficient is greater than or equal to the corresponding total pressure recovery coefficient index, and the absolute value of the relative deviation between the simulated airflow uniformity value and the uniformity index is less than or equal to the preset relative threshold. Then, the three-dimensional model of the inlet swirl adjustment device of the adjusted afterburner test piece is output.

7. The design method of the inlet swirl adjustment device for the afterburner test piece according to claim 6, characterized in that, The total pressure recovery coefficient index of the internal flow channel under the test operating conditions is based on the following: Analysis yielded, among which This represents the lower limit of the total pressure recovery coefficient for the internal flow channel corresponding to the current finite element simulation model. As the first coefficient, The value range is 0 to 1. The number of adjustable guide vanes in the internal flow channel. The maximum thickness of the adjustable guide vane blade. The length of the arc in the inner flow channel between the two guide vanes. To assess the incoming Mach number under the operating conditions.

8. The design method of the inlet swirl adjustment device for the afterburner test piece according to claim 6, characterized in that, The uniformity index of the internal flow channel under the condition of incoming flow is based on the following: Analysis yielded, among which This represents the lower limit of the uniformity of the internal flow channel corresponding to the current finite element simulation model. As the second coefficient, The value ranges from 1.5 to 2.

5. The number of adjustable guide vanes in the internal flow channel. The chord length of the adjustable guide vane, The length of the arc in the inner flow channel between the two guide vanes.

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