CN114658502B - Support sleeve, support mechanism and design method of support sleeve - Google Patents
Support sleeve, support mechanism and design method of support sleeve Download PDFInfo
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- CN114658502B CN114658502B CN202210336040.8A CN202210336040A CN114658502B CN 114658502 B CN114658502 B CN 114658502B CN 202210336040 A CN202210336040 A CN 202210336040A CN 114658502 B CN114658502 B CN 114658502B
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- 238000000034 method Methods 0.000 title claims abstract description 15
- 230000007246 mechanism Effects 0.000 title abstract description 26
- 230000008859 change Effects 0.000 claims abstract description 23
- 238000009434 installation Methods 0.000 claims abstract description 14
- 230000007704 transition Effects 0.000 claims description 9
- 230000008878 coupling Effects 0.000 claims description 4
- 238000010168 coupling process Methods 0.000 claims description 4
- 238000005859 coupling reaction Methods 0.000 claims description 4
- 238000011084 recovery Methods 0.000 description 6
- 238000011144 upstream manufacturing Methods 0.000 description 6
- 239000012530 fluid Substances 0.000 description 3
- 238000000926 separation method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
Abstract
The present disclosure provides a support sleeve, which is suitable for being arranged in a flow channel formed by a hub and a casing sleeved outside the hub, wherein the support sleeve forms a molded line of the support sleeve along a section in a direction orthogonal to a radial direction of the flow channel, the molded line comprises a front edge, a rear edge and a closed curve formed by connecting lines between the front edge and the rear edge, and a mounting angle of the molded line is gradually deflected along the radial direction of the flow channel so as to enable the support sleeve to twist along the radial direction of the flow channel, so as to adapt to a change of an airflow direction along the radial direction of the flow channel; wherein the installation angle is characterized by a rotation angle in a cross section along a direction orthogonal to the radial direction of the flow channel with a certain point of a connecting line of the center of the front edge and the center of the rear edge of the front edge as a center. The disclosure also provides a support mechanism comprising a hub, a casing and a support sleeve. The present disclosure also provides a design method suitable for designing a support sleeve.
Description
Technical Field
The disclosure relates to the technical field of gas turbines, and in particular relates to a support sleeve, a support mechanism and a design method of the support sleeve, which are suitable for being arranged in a flow channel formed by a hub and a casing sleeved outside the hub.
Background
The heavy gas turbine is a power device and comprises a multistage turbine and a diffuser arranged at the downstream of the turbine, wherein the diffuser is used for guiding airflow and recovering the residual speed kinetic energy of the final stage turbine.
The exhaust diffuser is a flow passage with gradually enlarged flow area formed by the inner cone and the outer cone, and the back pressure and the exhaust loss are reduced as much as possible by reducing the flow rate. A supporting sleeve is arranged between the inner cone body and the outer cone body and is used for supporting the inner cone body and the outer cone body. At present, the outer contour of the supporting sleeve adopts a certain airfoil structure, and the molded line and the installation angle of the supporting sleeve are kept the same along the radial direction of the flow channel. The upstream turbine has different blade loads and/or blade profiles, so that the flow direction of the turbine outlet is changed along the radial direction, and the turbine outflow direction is not matched with the shape of the supporting sleeve at the local radial height position, so that the attack angle is overlarge, flow separation is caused, and local flow loss is increased.
Disclosure of Invention
Aiming at the prior technical problems, the present disclosure provides a support sleeve for at least partially solving the technical problems.
According to an aspect of embodiments of the present disclosure, there is provided a support sleeve adapted to be disposed in a flow passage formed by a hub and a casing sleeved outside the hub, the support sleeve forming a molded line of the support sleeve along a section orthogonal to a radial direction of the flow passage, the molded line including a leading edge, a trailing edge, and a closed curve formed by a line connecting the leading edge and the trailing edge, a mounting angle of the molded line being gradually deflected in the radial direction of the flow passage so that the support sleeve is twisted in the radial direction of the flow passage to accommodate a change in an air flow direction in the radial direction of the flow passage; wherein the installation angle is characterized by a rotation angle in a cross section in a direction orthogonal to the radial direction of the flow passage centering on a certain point in a line connecting the center of the front edge and the center of the rear edge of the front edge.
In an exemplary embodiment, the support sleeve is divided into 7 or 11 sections at uniform intervals along the radial direction of the flow passage, and the angles of the mounting angles of the molded lines formed in at least two of the sections are different.
In an exemplary embodiment, the angle of attack of the leading edge of the support sleeve (1) in the radial direction of the flow channel is less than 5 °; wherein the leading edge angle of attack is characterized by a difference between an absolute airflow angle of the last stage turbine adjacent the flow path and the mounting angle.
In an exemplary embodiment, the support sleeve is rotated step by step from a mounting angle near the first end of the hub to a second end near the receiver, the mounting angle varying from 4.64 ° to 3.87 °.
According to another aspect of embodiments of the present disclosure, there is provided a support mechanism comprising: a hub; the casing is sleeved on the outer side of the hub, and a flow passage is formed between the hub and the casing; and the support sleeve is formed between the hub and the casing along the radial direction of the flow passage.
According to yet another aspect of embodiments of the present disclosure, there is provided a support sleeve design method adapted to design a support sleeve, constructing a three-dimensional coordinate system of an original support sleeve including a mounting angle; presetting a design working condition, calculating or measuring a coupling flow field of a final turbine and a diffuser under the design working condition, and acquiring change data of an absolute airflow angle of an outlet of the final turbine along a z-axis of the three-dimensional coordinate system; uniformly selecting a plurality of target positions at intervals along the z-axis, and fitting a change curve of the absolute airflow angle along the z-axis according to the change data of each target position; determining a first installation angle of a first molded line formed by a plurality of target positions on an xy section according to an absolute airflow angle corresponding to the change curve at the target position; fitting the first mounting angles to form a straight line, and calculating a second mounting angle of each first molded line, wherein each first molded line rotates in the xy section according to the corresponding second mounting angle to obtain a plurality of second molded lines; and stacking each second molded line and forming a smooth transition along the z-axis direction to form the target support sleeve.
In an exemplary embodiment, determining a first mounting angle of a first molded line formed by a plurality of target positions on an xy section according to an absolute airflow angle corresponding to the change curve at the target positions includes: establishing an equation including a leading edge angle of attack, an absolute airflow angle, and the first mounting angle; and calculating the first mounting angle by the equation on the condition that a leading edge attack angle of the target mounting sleeve is less than 5 °.
In an exemplary embodiment, stacking each of the second lines and forming a smooth transition along the z-axis direction to form the target support sleeve includes: taking a connecting line of the center of a second molded line or the center of a rear edge of the second supporting sleeve as an stacking line; stacking a plurality of second molded lines along a stacking line; and smooth transition is formed between the adjacent second molded lines.
In an exemplary embodiment, under the design condition, the leading edge attack angle of the third molded line formed on the xy section along the z-axis direction of the target support sleeve is checked to be less than 5 °.
According to the support sleeve and the support mechanism provided by the present disclosure, the support sleeve is configured to be distorted in the blade height direction of the superior turbine by the change of the installation angle in the radial direction of the flow passage. On the one hand, the device is suitable for adapting to the radial change of the air flow direction of the upstream turbine outlet, reduces the local flow separation generated by overlarge air flow attack angle at the casing and the hub, is beneficial to improving the diffusion capacity of the diffuser provided with the supporting sleeve and reduces the exhaust loss in the diffuser; on the other hand, the back pressure distribution control system can be more effectively suitable for the back pressure distribution of an upstream turbine, control the distribution of loads along the height of the blades, improve the internal flow of the upstream turbine, and improve the turbine efficiency, thereby improving the performance of the gas turbine unit.
According to the design method provided by the disclosure, the support sleeve meeting the corresponding front edge attack angle is designed according to the absolute airflow angle of the outlet of the upper-stage turbine.
Drawings
FIG. 1 is a perspective view of a support sleeve of an exemplary embodiment of the present disclosure;
FIG. 2 is a cross-sectional view of a profile of the support sleeve of the exemplary embodiment shown in FIG. 1;
FIG. 3 is a cross-sectional view of the absolute airflow angle and mounting angle of the illustrative embodiment shown in FIG. 2;
FIG. 4 is a linear plot of the angle of the mounting angle of the profile of the illustrative embodiment shown in FIG. 2 along the radial direction of the flow passage;
FIG. 5 is a perspective view of a support mechanism of an exemplary embodiment of the present disclosure;
FIG. 6 is a graph comparing pressure recovery coefficients of the exhaust system with and without the support sleeve of the support mechanism shown in FIG. 5;
FIG. 7 is a comparison of total pressure loss for the support mechanism shown in FIG. 5 with and without a support sleeve;
FIG. 8 is a flow chart of a design method of an illustrative embodiment of the present disclosure;
FIG. 9 is a perspective view of an exemplary embodiment of a support sleeve in a three-dimensional coordinate system;
FIG. 10 is a schematic view in xy coordinate system of the support sleeve of FIG. 9 with the center of the profile as the stacking line;
FIG. 11 is a perspective view of another illustrative embodiment of a support sleeve in a three-dimensional coordinate system; and
fig. 12 is a schematic view in xy coordinate system of the trailing edge center of the support sleeve shown in fig. 11 as a stacking line.
Reference numerals
1. A support sleeve;
11. a leading edge;
111. a center of a front edge;
12. a trailing edge;
121. a center of the rear edge;
2. a casing; and
3. a hub.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present disclosure more apparent, the technical solutions of the embodiments of the present disclosure will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present disclosure. It will be apparent that the described embodiments are some, but not all, of the embodiments of the present disclosure. All other embodiments, which can be made by one of ordinary skill in the art without the need for inventive faculty, are within the scope of the present disclosure, based on the described embodiments of the present disclosure.
Unless defined otherwise, technical or scientific terms used in this disclosure should be given the ordinary meaning as understood by one of ordinary skill in the art. The terms "first," "second," and the like, as used in this disclosure, do not denote any order, quantity, or importance, but rather are used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that elements or items preceding the word are included in the element or item listed after the word and equivalents thereof, but does not exclude other elements or items.
Descriptions of structural embodiments and methods of the present disclosure are disclosed herein. It should be understood that this disclosure is not intended to be limited to the particular disclosed embodiments, which can be practiced using other features, elements, methods and embodiments. Like elements in different embodiments are generally referred to by like numerals.
FIG. 1 is a perspective view of a support sleeve of an exemplary embodiment of the present disclosure; FIG. 2 is a cross-sectional view of a profile of the support sleeve of the exemplary embodiment shown in FIG. 1; FIG. 3 is a cross-sectional view of the absolute airflow angle and mounting angle of the illustrative embodiment shown in FIG. 2; fig. 4 is a linear plot of the angle of the mounting angle of the profile of the illustrative embodiment shown in fig. 2 along the radial direction of the flow channel.
In an exemplary embodiment of the present disclosure, as shown in fig. 1 to 4, a support sleeve 1 is provided, which is suitable for being disposed in a flow channel formed by a hub 3 and a casing 2 sleeved outside the hub 3, wherein a section of the support sleeve 1 along a direction orthogonal to a radial direction of the flow channel forms a molded line of the support sleeve 1, the molded line comprises a front edge 11, a rear edge 12 and a closed curve formed by connecting lines between the front edge and the rear edge, and a mounting angle of the molded line is gradually deflected along the radial direction of the flow channel, so that the support sleeve 1 is twisted along the radial direction of the flow channel to adapt to a change of an airflow direction along the radial direction of the flow channel. The installation angle is characterized by a rotation angle in a cross section in a direction orthogonal to the radial direction of the flow path about a certain point in a line connecting the leading edge center 111 of the leading edge and the trailing edge center 121 of the trailing edge.
In an exemplary embodiment, the angle of the installation angle of the molded lines at different positions is changed to ensure that the pipeline system and the instruments inside the supporting mechanism provided with the supporting sleeve 1 have a relatively sufficient channel space, and are suitable for the change of the upstream gas flow direction.
In an exemplary embodiment, the support sleeve 1 is inclined at a first inclination angle to the direction of the air flow.
In detail, the tilting means includes forward tilting or backward tilting. The forward tilt is characterized by the relative position of the second end (end near the casing) of the support sleeve in the axial direction of the flow passage being forward of the first end (end near the hub), and the backward tilt is characterized by the relative position of the second end of the support sleeve in the axial direction of the flow passage being backward of the first end.
Further, the first inclination angle is preferably adapted to the flow rate of the air flow.
In another exemplary embodiment, the support sleeve 1 is inclined at a second inclination angle to the circumferential direction of the flow channel.
In detail, the tilting means includes a clockwise tilting or a counterclockwise tilting. The clockwise tilt is characterized by the relative position of the second end of the support sleeve (end near the casing) in the radial direction of the flow channel being left compared to the first end (end near the hub), and the counterclockwise tilt is characterized by the relative position of the second end of the support sleeve (end near the casing) in the radial direction of the flow channel being right compared to the first end (end near the hub).
According to an embodiment of the present disclosure, the support sleeve 1 is divided into 7 or 11 sections at uniform intervals along the radial direction of the flow passage, and the angles of the installation angles of the molded lines formed in at least two of the sections are different.
In an exemplary embodiment, the support sleeve 1 is divided into 7 sections at even intervals in the radial direction of the flow channel, each section having a profile formed therein.
In detail, the installation angle of the molded line formed in each section is different.
Further, the angle of the installation angle from one end to the other end of the support sleeve 1 gradually increases.
According to an embodiment of the present disclosure, as shown in fig. 3, the angle of attack of the leading edge of the support sleeve 1 is less than 5 °. The leading edge angle of attack delta (r) is characterized by the difference between the absolute gas flow angle alpha (r) and the mounting angle beta (r) of the last stage turbine adjacent to the flow path.
In an exemplary embodiment, the leading edge angle of attack |δ (r) |= |α (r) - β (r) | <5 °. It should be understood that embodiments of the present disclosure are not limited thereto.
For example, the values of the leading edge angle of attack include, but are not limited to, values equal to 5 °, 5 ° to 10 °, 10 ° to 15 °, and other values or intervals. The specific embodiment is suitable for the radial change rule of the airflow angle of the final stage turbine outlet at the upstream of the supporting mechanism along the flow channel, and the local flow loss of the supporting sleeve 1 is preferably close to the minimum value under the condition of coupling the flow field.
According to an embodiment of the present disclosure, as shown in fig. 4, the support sleeve 1 is rotated step by step from a mounting angle near the first end of the hub 3 to a second end near the casing 2, and the range of the mounting angle includes-4.64 ° to 3.87 °.
In an exemplary embodiment, the support sleeves are divided into 7 sections at uniform intervals along the radial direction of the flow channel, and are adapted to form 7 molded lines.
In detail, the mounting angles of the 7 molded lines are shown in fig. 4, and the vertical axis in fig. 4 is characterized by the relative position on the support sleeve (0.0 represents one end of the support sleeve, and 1.0 represents the other end of the support sleeve); the horizontal axis represents the angle of the mounting angle; rectangular points are characterized by the computational fluid dynamics (Computational Fluid Dynamics) calculations; the straight line segment formed is characterized as the angle of the mounting angle after fitting according to the calculation result of the computational fluid dynamics.
In an exemplary embodiment, as shown in FIG. 2, the leading edge 11 is configured to have a radius (r) of 45 millimeters 1 ) The curvature of the leading edge 11 comprises 146 °.
In one illustrative embodiment, as shown in FIG. 2, the trailing edge 12 is configured to have a radius (r) of 45 millimeters 2 ) The curvature of the trailing edge 12 comprises 173 °.
FIG. 5 is a perspective view of a support mechanism of an exemplary embodiment of the present disclosure; FIG. 6 is a graph comparing pressure recovery coefficients of the exhaust system with and without the support sleeve of the support mechanism shown in FIG. 5; fig. 7 is a comparative view of total pressure loss of the support mechanism shown in fig. 5 with and without the support sleeve.
In another exemplary embodiment of the present disclosure, as shown in fig. 5, there is also provided a support mechanism including a hub 3, a casing 2, and a support sleeve 1. The casing 2 is sleeved outside the hub 3, and a flow passage is formed between the hub 3 and the casing 2. The support sleeve 1 is formed between the hub 3 and the casing 2 in the radial direction of the flow passage.
In one illustrative embodiment, the exhaust system pressure recovery factor comparison is based on a support mechanism with a support sleeve mounted and a support mechanism without a support sleeve mounted.
In detail, as shown in fig. 6, the ordinate is characterized by a pressure coefficient, and the abscissa is characterized by a flow coefficient.
Further, the solid line in fig. 6 is characterized by a pressure recovery coefficient curve of the support mechanism with the support sleeve mounted thereon, and the broken line is characterized by a pressure recovery coefficient curve of the support mechanism without the support sleeve mounted thereon. As in the embodiment shown in fig. 5, it can be seen that the pressure recovery coefficient of the exhaust system of the support mechanism to which the support sleeve is attached gradually increases.
In one illustrative embodiment, a total pressure loss comparison is made based on a support mechanism with a support sleeve mounted and a support mechanism without a support sleeve mounted.
In detail, as shown in fig. 7, the ordinate is characterized by loss, and the abscissa is characterized by flow coefficient.
Further, the solid line in fig. 7 is characterized by the total pressure loss curve of the support mechanism with the support sleeve installed, and the broken line is characterized by the total pressure loss curve of the support mechanism without the support sleeve installed. As in the embodiment shown in fig. 7, it can be seen that the total pressure loss of the support mechanism with the support sleeve mounted thereon is gradually reduced.
FIG. 8 is a flow chart of a design method of an illustrative embodiment of the present disclosure; FIG. 9 is a perspective view of an exemplary embodiment of a support sleeve in a three-dimensional coordinate system; FIG. 10 is a schematic view in xy coordinate system of the support sleeve of FIG. 9 with the center of the profile as the stacking line; FIG. 11 is a perspective view of another illustrative embodiment of a support sleeve in a three-dimensional coordinate system; fig. 12 is a schematic view in xy coordinate system of the trailing edge center of the support sleeve shown in fig. 11 as a stacking line.
In another exemplary embodiment of the present disclosure, as shown in fig. 8 to 12, there is also provided a method of designing a support sleeve 1, including constructing a three-dimensional coordinate system of an original support sleeve 1 including a mounting angle; presetting a design working condition, calculating or measuring a coupling flow field of a final-stage turbine and a supporting mechanism under the design working condition, and acquiring change data of an absolute airflow angle (alpha (r)) of an outlet of the final-stage turbine along a z-axis of a three-dimensional coordinate system; uniformly selecting a plurality of target positions at intervals along the z axis, and fitting a change curve of the absolute air flow angle along the z axis according to the change data of each target position; determining a first installation angle (beta (r)) of a first molded line formed by a plurality of target positions on an xy section according to an absolute airflow angle corresponding to the change curve at the target positions; fitting the first mounting angles to form a straight line, and calculating a second mounting angle of each first molded line, wherein each first molded line rotates in the xy section according to the corresponding second mounting angle to obtain a plurality of second molded lines; the second lines are stacked and form smooth transition along the z-axis direction to form the target support sleeve 1.
In an exemplary embodiment, as shown in fig. 9, the three-dimensional coordinate system of the original support sleeve 1 constructed to include the mounting angle includes an oxyz coordinate system.
In detail, the absolute air flow angle (α (r)) is formed in the xy section in a direction orthogonal to the z axis.
According to an embodiment of the disclosure, determining a first mounting angle of a first molded line formed by a plurality of target positions on an xy section according to an absolute airflow angle corresponding to the target positions of a change curve comprises establishing an equation comprising a leading edge attack angle, the absolute airflow angle and the first mounting angle; the first mounting angle is calculated by the equation on the condition that the leading edge attack angle of the target mounting sleeve is less than 5 °.
In an exemplary embodiment, the leading edge angle of attack |δ (r) |= |α (r) - β (r) | <5 °.
According to an embodiment of the present disclosure, as shown in fig. 9 to 12, stacking each second molded line and forming a smooth transition along the z-axis direction to form the target support sleeve 1 includes taking a line of the center of the second molded line or the center of the trailing edge of the second support sleeve 1 as a stacking line; stacking a plurality of second molded lines along a stacking line; a smooth transition is formed between adjacent second molded lines.
In an exemplary embodiment, as shown in fig. 9 and 10, a plurality of second molded lines are stacked with a line connecting the center of the molded lines of the second support sleeve 1 as a stacking line.
In detail, the stacking is characterized by orthographically projecting a plurality of second lines in an xy coordinate system along the z-axis extension direction with stacking lines as points of engagement.
Further, 7 second molded lines formed in 7 sections including section 1 to section 7 are included.
In an exemplary embodiment, as shown in fig. 11 and 11, a plurality of second molded lines are stacked with a line connecting the center of the rear edge of the second support sleeve 1 as a stacking line.
In detail, the stacking is characterized by orthographically projecting a plurality of second lines in an xy coordinate system along the z-axis extension direction with stacking lines as points of engagement.
Further, 7 second molded lines formed in 7 sections including section 1 to section 7 are included.
According to the embodiment of the present disclosure, under the design condition, the leading edge attack angle (δ' (r)) of the third molded line formed on the xy section in the z-axis direction of the inspection target support sleeve 1 is less than 5 °.
Those skilled in the art will appreciate that the features recited in the various embodiments of the disclosure and/or in the claims may be provided in several combinations or combinations, even if such combinations or combinations are not explicitly recited in the disclosure. In particular, the features recited in the various embodiments of the present disclosure and/or the claims may be combined and/or combined in several ways without departing from the spirit and teachings of the present disclosure. All such combinations and/or combinations fall within the scope of the present disclosure.
While the foregoing embodiments have been described in some detail for purposes of clarity of understanding, it will be understood that the foregoing embodiments are merely illustrative of the invention and are not intended to limit the invention, any modifications, equivalents, improvements, etc. that fall within the spirit and principles of the present disclosure are intended to be included within the scope of the present disclosure.
Claims (4)
1. A support sleeve design method suitable for a support sleeve design, comprising:
constructing a three-dimensional coordinate system of an original support sleeve containing the installation angle;
presetting a design working condition, calculating or measuring a coupling flow field of a final turbine and a diffuser under the design working condition, and acquiring change data of an absolute airflow angle of an outlet of the final turbine along a z-axis of the three-dimensional coordinate system;
uniformly selecting a plurality of target positions at intervals along the z-axis, and fitting a change curve of the absolute airflow angle along the z-axis according to the change data of each target position;
determining a first installation angle of a first molded line formed by a plurality of target positions on an xy section according to an absolute airflow angle corresponding to the change curve at the target position;
fitting the first mounting angles to form a straight line, and calculating a second mounting angle of each first molded line, wherein each first molded line rotates in the xy section according to the corresponding second mounting angle to obtain a plurality of second molded lines; and
stacking each second line and forming smooth transition along the z-axis direction to form a target support sleeve;
the support sleeve (1) is suitable for being arranged in a flow passage formed by a hub (3) and a casing (2) sleeved outside the hub (3), and is characterized in that a section of the support sleeve (1) along the direction orthogonal to the radial direction of the flow passage forms a molded line of the support sleeve (1), the molded line comprises a front edge (11), a rear edge (12) and a closed curve formed by connecting lines between the front edge and the rear edge, and the mounting angle of the molded line is gradually deflected along the radial direction of the flow passage, so that the support sleeve (1) is twisted along the radial direction of the flow passage to adapt to the change of the air flow direction along the radial direction of the flow passage;
wherein the installation angle is characterized by a rotation angle in a cross section in a direction orthogonal to the radial direction of the flow passage about a certain point in a line connecting a leading edge center (111) of the leading edge and a trailing edge center (121) of the trailing edge.
2. The method according to claim 1, wherein determining a first mounting angle of a first molded line formed by the plurality of target positions on an xy section based on an absolute air flow angle corresponding to the change curve at the target position, comprises:
establishing an equation including a leading edge angle of attack, an absolute airflow angle, and the first mounting angle; and
the first mounting angle is calculated by the equation on the condition that a leading edge attack angle of the target supporting sheath is less than 5 °.
3. The method of designing according to claim 1, wherein stacking each of the second lines and forming a smooth transition along the z-axis direction to form the target support sleeve includes:
taking a connecting line of the center of the second molded line or the center of the rear edge of the target supporting sleeve as an stacking line;
stacking a plurality of second molded lines along a stacking line; and
a smooth transition is formed between adjacent second molded lines.
4. A design method according to any one of claims 1-3, characterized in that, under the design conditions, the leading edge attack angle of the third line of the target support sleeve (1) formed in the xy-section in the z-axis direction is checked to be smaller than 5 °.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210336040.8A CN114658502B (en) | 2022-03-31 | 2022-03-31 | Support sleeve, support mechanism and design method of support sleeve |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210336040.8A CN114658502B (en) | 2022-03-31 | 2022-03-31 | Support sleeve, support mechanism and design method of support sleeve |
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| CN114658502A CN114658502A (en) | 2022-06-24 |
| CN114658502B true CN114658502B (en) | 2023-12-26 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2644846A1 (en) * | 2012-03-30 | 2013-10-02 | Alstom Technology Ltd | Exhaust diffuser for a gas turbine |
| CN108386389A (en) * | 2018-02-08 | 2018-08-10 | 中国科学院工程热物理研究所 | A kind of centrifugal compressor diffuser structure that blade is blended with casing and wheel hub |
| CN111315964A (en) * | 2017-09-26 | 2020-06-19 | Gkn航空公司 | Recess for an outer housing shroud |
| DE102020130637A1 (en) * | 2019-11-20 | 2021-05-20 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Transition channel for a turbo machine as well as a turbo machine |
-
2022
- 2022-03-31 CN CN202210336040.8A patent/CN114658502B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2644846A1 (en) * | 2012-03-30 | 2013-10-02 | Alstom Technology Ltd | Exhaust diffuser for a gas turbine |
| CN111315964A (en) * | 2017-09-26 | 2020-06-19 | Gkn航空公司 | Recess for an outer housing shroud |
| CN108386389A (en) * | 2018-02-08 | 2018-08-10 | 中国科学院工程热物理研究所 | A kind of centrifugal compressor diffuser structure that blade is blended with casing and wheel hub |
| DE102020130637A1 (en) * | 2019-11-20 | 2021-05-20 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Transition channel for a turbo machine as well as a turbo machine |
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|---|---|
| CN114658502A (en) | 2022-06-24 |
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