CN117662253A - Pneumatic layout design method for serial blades of exhaust support plate of high-through-flow wide-working-condition turbine - Google Patents
Pneumatic layout design method for serial blades of exhaust support plate of high-through-flow wide-working-condition turbine Download PDFInfo
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- CN117662253A CN117662253A CN202311567227.XA CN202311567227A CN117662253A CN 117662253 A CN117662253 A CN 117662253A CN 202311567227 A CN202311567227 A CN 202311567227A CN 117662253 A CN117662253 A CN 117662253A
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Abstract
The invention provides a pneumatic layout design method of a serial blade of a turbine exhaust support plate under a high-through-flow wide working condition, which realizes the pneumatic rectification function of a turbine exhaust section through two rows of blades; the hub profile of the turbine exhaust section is an S-shaped curve; the casing molded line of the turbine exhaust section is in a convex hull shape, and the axial position of the highest point of the convex hull is the same as the axial position of the maximum thickness of the front row of blades. The invention is suitable for working conditions with the characteristics of high incoming flow Mach number, wide attack angle change range, remarkable meridian flow passage expansion and the like, can meet the functions of rectifying, bearing force, force transmission, air entraining and the like borne by the turbine exhaust section in structural aspect, and can realize low loss and rectifying requirements in pneumatic aspect.
Description
Technical Field
The invention belongs to the technical field of turbine engines, and particularly relates to a pneumatic layout design method for serial blades of a high-through-flow wide-working-condition turbine exhaust support plate.
Background
The novel turbine engine is used for reducing weight and cost, requires higher turbine load and adopts fewer stages, so that the inlet pre-rotation of the turbine exhaust section rectifying support plate is higher, and the pneumatic design difficulty is increased. Because of the wide working range of the turbine part, the Mach number change range of the turbine outlet reaches 0.4-0.7, the air flow angle change range reaches +/-15 degrees, larger radial change exists from root to tip, and the outlet support plate is required to bear functions of rectification, bearing force, force transmission, air entraining and the like, so that the maximum thickness and the leaf area of the support plate are limited, and the expansion of the exhaust section channel is often obvious. Under the requirement of high compact structure, the channel expansion degree is aggravated. Under the above-described inflow conditions and structural limitations, the exhaust manifold is extremely susceptible to flow separation, thereby presenting significant difficulties in the stable operation of the downstream afterburner. Meanwhile, as the working time of the forced combustion chamber in the novel turbine engine is long and the influence on the whole thrust is large, the quality of the flow field of the support plate outlet must be strictly controlled in the design. Therefore, designing turbine exhaust sections with high axial Mach numbers, large angles of attack, and small axial dimensions is a challenge. FIG. 1 is a radial distribution of inlet gas flow angles to the exhaust section of a turbine under two typical operating conditions.
Disclosure of Invention
First, the technical problem to be solved
The invention provides a pneumatic layout design method for serial blades of a turbine exhaust support plate under a high-through-flow wide working condition, which aims at the characteristics of high incoming flow Mach number, wide attack angle change range, large meridian passage expansion, compact axial size and the like, so as to solve the technical problems of how to realize support of the support plate, provide a pipeline/cold air passage, and low loss and rectification.
(II) technical scheme
In order to solve the technical problems, the invention provides a pneumatic layout design method for serial blades of a turbine exhaust support plate under a high-through-flow wide working condition, and the pneumatic layout design method for the serial blades of the turbine exhaust support plate realizes the pneumatic rectification function of a turbine exhaust section through two rows of blades; the hub profile of the turbine exhaust section is an S-shaped curve; the casing molded line of the turbine exhaust section is in a convex hull shape, and the axial position of the highest point of the convex hull is the same as the axial position of the maximum thickness of the front row of blades; the number of front row blades is 9, the number of rear row blades is 27, the central angles of the three blades of the rear row relative to the front row blades are 3.33 degrees, 16.67 degrees and 30 degrees respectively, the axial length of the front row blades is 115mm, the axial length of the rear row blades is 50mm, and the axial distance between the front row blades and the rear row blades is 0mm.
Further, the hub molded Line and the casing molded Line are designed by utilizing a Line-Bezier-Line curve form.
Further, the convex hull height of the casing profile is 8.1mm.
Further, the axial position of the highest point of the convex hull is 50.0mm from the front row of blades.
Further, the rear row of blades are designed into straight blades, and the blade shapes of the root, middle and tip sections are consistent.
(III) beneficial effects
The invention provides a pneumatic layout design method of a serial blade of a turbine exhaust support plate under a high-through-flow wide working condition, which realizes the pneumatic rectification function of a turbine exhaust section through two rows of blades; the hub profile of the turbine exhaust section is an S-shaped curve; the casing molded line of the turbine exhaust section is in a convex hull shape, and the axial position of the highest point of the convex hull is the same as the axial position of the maximum thickness of the front row of blades. The invention is suitable for working conditions with the characteristics of high incoming flow Mach number, wide attack angle change range, remarkable meridian flow passage expansion and the like, can meet the functions of rectifying, bearing force, force transmission, air entraining and the like borne by the turbine exhaust section in structural aspect, and can realize low loss and rectifying requirements in pneumatic aspect.
Drawings
FIG. 1 is a radial distribution of inlet gas flow angles of a turbine exhaust section under typical operating conditions;
FIG. 2 is a schematic illustration of a turbine exhaust manifold noon flow path and profile parameterization;
FIG. 3 is a schematic view of a turbine exhaust manifold forward row vane profile;
FIG. 4 is a schematic view of a turbine exhaust manifold aft row blade profile;
FIG. 5a is a schematic representation of a aerodynamic layout of a root section of a turbine exhaust strut tandem blade, FIG. 5b is a schematic representation of a aerodynamic layout of a root mid-plane, and FIG. 5c is a schematic representation of a aerodynamic layout of a tip section;
FIG. 6 is a schematic view of the definition of the center angle of the front and rear rows of blades in the aerodynamic layout of the turbine exhaust support plate tandem blades;
FIG. 7 is an exit airflow angular distribution for a turbine exhaust cascade vane aerodynamic layout optimum design.
Detailed Description
To make the objects, contents and advantages of the present invention more apparent, the following detailed description of the present invention will be given with reference to the accompanying drawings and examples.
The invention provides a pneumatic layout design method for a serial blade of a turbine exhaust support plate under a high-flow-width working condition, wherein the basic design thought of pneumatic layout of the serial blade of the exhaust support plate is to realize the pneumatic rectification function of an exhaust section of the turbine through two rows of blades, reduce the pneumatic design difficulty of the support plate, and mainly research the consistency of the support plate, the chord length of the blade profile, the maximum thickness position, the installation angle, the axial distance between the upstream blade row and the downstream blade row, the circumferential position and other blade profile design parameters. The requirements of the turbine exhaust section on the structural aspect, such as supporting, providing a pipeline/cold air passage and the like, are realized through the front-row blades, and the space is expanded for the design freedom degree of the rear-row blades, so that the rear-row blades can be designed by adopting advanced three-dimensional pneumatic modeling technologies such as bending, sweeping and the like, the flow loss is reduced as much as possible, and the rectifying requirement is met.
Firstly, according to the technical requirements of the design of the support plate, particularly the constraint and the limitation in the aspect of structural dimension, which are provided by the turbine exhaust section under the high-through-flow wide working condition, the design of the noon runner molded line and the front-row blades of the exhaust section is completed, as shown in fig. 2.
As a downstream component of the low pressure turbine, inlet aerodynamic boundary conditions and geometry of the turbine exhaust section are substantially determined; as an upstream component of the afterburner, in particular in new turbine engines, the afterburner has a long operating time and a large impact on the overall thrust forces, the quality of the outlet flow field of the exhaust section must be strictly controlled in design and its outlet geometry is also generally limited to a range. Furthermore, the turbine exhaust section is small in axial dimension and substantially defined under high compact structural constraints. Therefore, meridian runner profile design is one of the important things for turbine exhaust sections with very limited design freedom. Specifically, the exhaust section hub or rim profile is designed in a reasonably curvilinear fashion to attenuate end wall flow separation and loss, depending on specific structural parameter constraints and limitations. Since the turbine exhaust section inlet/outlet inner diameter size is substantially determined and the main expansion area of the meridian passage is located at the hub location, the design of the hub profile is important for the exhaust section. As shown in FIG. 2, the hub molded Line is designed into an S-shaped curve by utilizing a Line-Bezier-Line curve form, the starting point and the ending point of the hub molded Line are gentle, the middle is steep, the first inflection point is close to the front edge of the front row of blades, and the second inflection point is positioned near the position of the maximum thickness of the front row of blades, so that the expansion of the vast majority of meridian runners is realized before the second inflection point. The curve change form fully considers the influence of the thickness change of the front row of blades on the flow passage area, the thickness of the blades is gradually increased at the upstream of the maximum thickness position of the blades, and the radial flow passage is rapidly expanded, but the reduction of the flow area of the S1 flow surface (the rotation surface obtained by rotating around the axis of the engine) can play a certain area compensation role, so that the adverse effect brought by the radial flow passage is weakened; downstream of the maximum thickness position of the blade, the thickness of the blade is rapidly reduced, so that the flow area of the S1 flow surface is rapidly expanded, and the meridian runner is basically not expanded any more, thereby weakening the adverse effect caused by the reduction of the thickness of the blade. In addition, the radius of curvature of the first inflection point position is relatively small, so that the meridian flow channel rapidly expands at the upstream of the maximum thickness position of the front-row blades, and the radius of curvature of the second inflection point position is large, so that the meridian flow channel slowly changes at the position near and downstream of the maximum thickness position of the front-row blades, and flow deterioration caused by rapid line change is avoided.
Since the outer diameter dimensions of the turbine exhaust section inlet/outlet have been substantially determined, the design of the casing profile also has a significant impact on the flow characteristics in the upper half-lobe region of the exhaust section. The invention utilizes the Line-Bezier-Line curve to set the molded Line of the casingIn the shape of a convex hull, a channel form of expanding and contracting firstly is established in the area, so that the casing molded line is moderately pressed down after the maximum thickness of the front row of blades, and the separation of the expansion section at the rear part of the runner due to the reverse pressure gradient is expected to be relieved by utilizing the local acceleration caused by the contraction of the meridian runner. The height of the convex hull and the axial position of the highest point of the convex hull are two key control parameters of the casing type line. The convex hull height design is carried out by combining local flow characteristics, so that local flow separation caused by overlarge convex hull height is avoided on one hand, and the situation that the upper half-leaf high flow characteristics cannot be improved due to overlarge convex hull height is avoided at the same time, wherein the convex hull height is L 1 =8.1 mm. In order to fully exert the compensation effect of the curve shrinkage of the casing on the noon flow passage area, the axial position design of the highest point of the convex hull is carried out by combining the thickness change rule of the front-row blades, and the axial position of the highest point of the convex hull is basically consistent with the axial position of the maximum thickness of the front-row blades, namely the axial position of the highest point of the convex hull is far from the front edge L of the front-row blades 2 ＝50.0mm。
The number of front row blades or their extent is generally given by the engine as a whole before the aerodynamic design, due to structural strength and weight reduction requirements. Because the exhaust support plate also needs to meet the requirements of bearing force, passing through a cold air/oil supply pipeline and the like in terms of structure, the maximum thickness and the stacking mode of the exhaust support plate are basically determined. Therefore, the design space of the front row of blades is also very limited, mainly the blade profile parameters. In view of the small axial spacing of the leading row of blades from the upstream rotor, the leading edge radius should not be too large to avoid enhancing potential interference with the upstream rotor, while the larger trailing edge thickness is beneficial to improving the pressure gradient in the trailing half of the flow path. In order to reduce the friction loss of the blades, the number of the front row of blades is reduced as much as possible on the premise of meeting the structural requirement, and the number of the front row of blades is N in the invention 1 =9. Meanwhile, on the premise of structural permission, blade profile parameters such as inlet/outlet geometric construction angle, installation angle and the like of the front row of blades are designed according to incoming flow attack angle and rectification requirement, so that the front row of blades can play a role in rectification to a certain extent, as shown in fig. 3.
Secondly, on the basis of completing the design of the turbine exhaust section noon runner molded lines and the front row blades, the design of the aerodynamic layout scheme of the serial blades can be developed, and the main contents of the aerodynamic layout scheme are the blade profile design and the three-dimensional modeling design of the rear row blades and the design of the circumferential positions, the axial lengths and the axial distances of the front row blades and the rear row blades.
In order to realize good rectifying effect by utilizing the rear-row blades, the number of the rear-row blades is increased as much as possible, and the number of the rear-row blades is N in the invention 2 =27; in order to minimize blade friction losses, the trailing row of blades should be as thin as possible. Meanwhile, in order to reduce the manufacturing and processing difficulty, the rear row of blades are designed into straight blades, and the blade shapes of the root, the middle and the tip sections are consistent, as shown in fig. 4.
Fig. 5 a-5 c are schematic views of the aerodynamic layout of the exhaust support plate root, middle and tip section blade profile of a serial blade. The main design parameters of the aerodynamic layout of the tandem blades include the circumferential position, axial length, and axial spacing of the front and rear rows of blades. On the premise that design parameters of front and rear rows of blades are unchanged, the circumferential position, the axial length and the axial distance of the front and rear rows of blades are changed, the aerodynamic performance, the rectifying effect and the flow characteristic of the exhaust support plate are influenced, and the influence effect is closely related to specific working conditions. One is to determine the circumferential position of the front and rear row of blades. In order to study the influence of the circumferential positions of the front and rear rows of blades on the aerodynamic layout of the serial blades, the circumferential positions of the front row of blades are fixed, and different schemes of design are completed by changing the circumferential positions of the rear row of blades relative to the front row of blades. The circumferential relationship between the front row of blades and the rear row of blades is defined by adopting the corresponding central angle of the front row and the rear row of blades, as shown in fig. 6, the large blades correspond to the front row of blades, the small blades correspond to the rear row of blades, the circumferential positions of the front row and the rear row of blades are changed on the premise that the design parameters of the front row and the rear row of blades are unchanged, the aerodynamic performance and the outlet airflow angle of the exhaust support plate are influenced, and the influence effect is related to specific working conditions. The aerodynamic performance, the rectifying effect and the flow characteristic of the exhaust support plate are comprehensively considered, and the central angles of the three blades of the rear row relative to the blades of the front row are respectively 3.33 degrees, 16.67 degrees and 30 degrees.
And the other is to determine the axial length of the front and rear rows of blades. For the aerodynamic layout of the tandem blades, on the premise that the axial total length of the exhaust support plate is fixed, the length distribution of the front and rear rows of blades is also one of key design parameters. The optimal circumferential positions of front and rear rows of blades are pneumatically distributed by using serial blades as references, and on the premise that the blade profile design parameters of the front and rear rows of blades are basically unchanged (the number of the front and rear rows of blades is kept unchanged, the number of the front row of blades is 9, and the number of the rear row of blades is 27), and the axial distance between the front and rear rows of blades is kept unchanged, the design of a research scheme is developed by changing the axial length distribution of the front and rear rows of blades. The research results show that on the premise of unchanged axial total length of the exhaust support plate, increasing the axial length of the front row of blades and reducing the axial length of the rear row of blades are beneficial to improving the aerodynamic performance of the exhaust support plate, but the change of the rectifying control effect is related to specific working conditions. The aerodynamic performance, the rectifying effect and the flow characteristic of the exhaust support plate are comprehensively considered, and the axial length of the front row of blades is 115mm and the axial length of the rear row of blades is 50mm.
Thirdly, the axial distance between the front row of blades and the rear row of blades is determined. For the aerodynamic layout of the tandem blades, on the premise that the axial total length of the exhaust support plate is fixed, the axial distance between the front row of blades and the rear row of blades is also one of key design parameters. The optimal circumferential positions and the axial lengths of the front row of blades and the rear row of blades are used as references, and on the premise that the blade profile design parameters of the front row of blades and the rear row of blades are basically unchanged (the number of the front row of blades and the rear row of blades is kept unchanged, the number of the front row of blades is 9, and the number of the rear row of blades is 27), the design of a research scheme is developed by changing the axial distance between the front row of blades and the rear row of blades. Research results show that on the premise that the axial length of the front row of blades and the axial distance of the rear row of blades are unchanged, the reduction of the axial distance of the front row of blades and the rear row of blades is beneficial to improving the rectifying effect of the exhaust support plate, but the influence on the aerodynamic performance of the exhaust support plate is related to specific working conditions. The aerodynamic performance, the rectifying effect and the flow characteristic of the exhaust support plate are comprehensively considered, and the axial distance between the front row of blades and the rear row of blades is 0mm.
The method can not only meet the functions of rectifying, bearing force, force transmission, air entraining and the like born by the turbine exhaust section in structural aspect, but also realize the low loss and rectifying requirements in pneumatic aspect. The turbine exhaust cascade blade aerodynamic layout optimum design outlet airflow angle distribution is shown in fig. 7.
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that modifications and variations could be made by those skilled in the art without departing from the technical principles of the present invention, and such modifications and variations should also be regarded as being within the scope of the invention.
Claims (5)
1. A pneumatic layout design method for a serial blade of a turbine exhaust support plate under a high-through-flow wide working condition is characterized in that the pneumatic layout design method for the serial blade of the turbine exhaust support plate realizes the pneumatic rectification function of a turbine exhaust section through two rows of blades; the hub profile of the turbine exhaust section is an S-shaped curve; the casing molded line of the turbine exhaust section is in a convex hull shape, and the axial position of the highest point of the convex hull is the same as the axial position of the maximum thickness of the front row of blades; the number of front row blades is 9, the number of rear row blades is 27, the central angles of the three blades of the rear row relative to the front row blades are 3.33 degrees, 16.67 degrees and 30 degrees respectively, the axial length of the front row blades is 115mm, the axial length of the rear row blades is 50mm, and the axial distance between the front row blades and the rear row blades is 0mm.
2. The method for aerodynamic layout design of a turbine exhaust support plate serial blade according to claim 1, wherein the hub profile and the casing profile are designed in a Line-Bezier-Line curve form.
3. The turbine exhaust support plate serial blade aerodynamic layout design method of claim 1, wherein the convex hull height of the casing profile is 8.1mm.
4. The method for aerodynamic layout design of a turbine exhaust support plate serial blade according to claim 1, wherein the axial position of the highest point of the convex hull is 50.0mm from the front edge of the front row of blades.
5. The aerodynamic layout design method of turbine exhaust support plate serial blades according to claim 1, wherein the rear row of blades are designed as straight blades, and the blade profiles of the root, middle and tip sections are consistent.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311567227.XA CN117662253A (en) | 2023-11-22 | 2023-11-22 | Pneumatic layout design method for serial blades of exhaust support plate of high-through-flow wide-working-condition turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311567227.XA CN117662253A (en) | 2023-11-22 | 2023-11-22 | Pneumatic layout design method for serial blades of exhaust support plate of high-through-flow wide-working-condition turbine |
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