CN116090137A - Turbine blade, turbine blade design method and apparatus - Google Patents
Turbine blade, turbine blade design method and apparatus Download PDFInfo
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- CN116090137A CN116090137A CN202310260281.3A CN202310260281A CN116090137A CN 116090137 A CN116090137 A CN 116090137A CN 202310260281 A CN202310260281 A CN 202310260281A CN 116090137 A CN116090137 A CN 116090137A
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
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- 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
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- 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
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
Abstract
The invention discloses a turbine blade, a turbine and a turbine blade design method and equipment, wherein the turbine blade design method comprises a blade outlet section axial wrap angle design step, and the blade outlet section axial wrap angle design step comprises the step of sequentially confirming wrap angle design values in the axial direction. In the turbine blade design method provided by the application, the wrap angle optimization control of each axial direction is performed on the blade outlet section according to the requirement of the flow field, and meanwhile when the difference value of the change of the over wrap angle exceeds the preset position, the difference value of the adjacent wrap angles is used as the wrap angle value on the corresponding layer of the blade, so that the condition that the larger stress is caused due to too large change of the degree is avoided, and the reliability is influenced.
Description
Technical Field
The invention relates to the technical field of turbine airflow control, in particular to a turbine design method. The invention also relates to a turbine blade design apparatus. The invention also relates to a turbine blade and a turbine manufactured by the method.
Background
In order to ensure that the impeller has higher mechanical performance during turbine design, the wrap angle of the part of the impeller, which is close to the outlet section, in the turbine is controlled.
As shown in fig. 1 below, the wrap angles of the blade outlet sections are the same in the same circumferential coordinate along the axial direction, so that the control of the blade angles is limited, the blade angles of each layer cannot be optimally controlled according to the requirements of the flow fields, and only the flow fields below a certain layer of the blade can be controlled to be optimal, so that the optimal performance cannot be ensured.
Therefore, how to ensure the performance and balance with the strength of turbine blades is a technical problem that the skilled person is urgent to solve.
Disclosure of Invention
The invention aims to provide a turbine blade design method. It is a further object of the present invention to provide a turbine blade, a turbine blade design apparatus.
In order to achieve the above object, the present invention provides a turbine blade designing method, including a blade outlet section axial wrap angle designing step, the blade outlet section axial wrap angle designing step including:
the blade outlet section obtains a plurality of target points along the current axial direction, and obtains wrap angle optimal values corresponding to the target points;
taking one of the target points as an initial target point, and taking a wrap angle optimal value corresponding to the initial target point as a wrap angle design value;
sequentially determining the wrap angle design values of other target points along the distance from the initial target point, wherein when the wrap angle optimal value of the current target point is larger than the wrap angle design value of the previous target point and exceeds a preset value, the wrap angle design value of the current target point is the sum of the wrap angle design value of the previous target point and the preset value; when the optimal value of the wrap angle of the current target point is smaller than or equal to the design value of the wrap angle of the previous target point and exceeds a preset value, the design value of the wrap angle of the current target point is the difference between the design value of the wrap angle of the previous target point and the preset value; and when the difference value between the wrap angle optimal value of the current target point and the wrap angle design value of the previous target point is smaller than the preset value, the wrap angle design value of the current target point is the wrap angle optimal value of the current target point.
Optionally, in the turbine blade design method, the method includes sequentially calculating the axial wrap angles of a plurality of blade outlet sections.
Optionally, in the turbine blade design method, the distance between two adjacent target points is equal.
Optionally, in the above turbine blade designing method, calculating the wrap angle optimum value includes the steps of:
acquiring the impeller speed U on a turbine blade target point;
acquiring the speed C of the airflow on the target point of the turbine blade in the meridian plane direction;
calculating a relative velocity flow angle β, β=arctan (U/C) at the turbine blade target point;
calculating an optimal value alpha of the wrap angle, wherein theta=arctan (R x dα/dm), wherein theta is the blade angle on the target point, R is the radius of the impeller, d is the derivative, m is the projection length of the preset position of the turbine blade on the meridian plane, and beta=theta.
Optionally, in the turbine blade design method, the distance between two adjacent target axes on the same blade outlet section is equal.
Optionally, in the turbine blade design method, the initial target point is a first target point of a blade outlet section near a shroud position.
Optionally, in the turbine blade design method described above, the preset value is 8 ° -12 °.
A turbine blade design apparatus comprising:
the data acquisition module is used for acquiring wrap angle optimal values corresponding to all target points;
the wrap angle value module is used for taking one of the target points as an initial target point, and the wrap angle optimal value corresponding to the initial target point is taken as a wrap angle design value; sequentially determining the wrap angle design values of other target points along the distance from the initial target point, wherein when the wrap angle optimal value of the current target point is larger than the wrap angle design value of the previous target point and exceeds a preset value, the wrap angle design value of the current target point is the sum of the wrap angle design value of the previous target point and the preset value; when the optimal value of the wrap angle of the current target point is smaller than or equal to the design value of the wrap angle of the previous target point and exceeds a preset value, the design value of the wrap angle of the current target point is the difference between the design value of the wrap angle of the previous target point and the preset value; and when the difference value between the wrap angle optimal value of the current target point and the wrap angle design value of the previous target point is smaller than the preset value, the wrap angle design value of the current target point is the wrap angle optimal value of the current target point.
Optionally, in the above turbine blade design apparatus, the turbine blade design apparatus further includes a wrap angle calculating module, where the wrap angle calculating module is configured to calculate a wrap angle optimal value, and the wrap angle calculating module obtains an impeller speed U on a turbine blade target point; acquiring the speed C of the airflow on the target point of the turbine blade in the meridian plane direction; calculating a relative velocity flow angle β, β=arctan (U/C) at the turbine blade target point; calculating an optimal value alpha of the wrap angle, wherein theta=arctan (R x dα/dm), wherein theta is the blade angle on the target point, R is the radius of the impeller, d is the derivative, m is the projection length of the preset position of the turbine blade on the meridian plane, and beta=theta.
A turbine blade obtained by the turbine blade design method as set forth in any one of the above.
A turbine, the turbine blades of which are obtained by the turbine blade design method as described in any one of the above.
In the above technical solution, the turbine blade design method provided by the present invention includes a blade outlet section axial wrap angle design step, and the blade outlet section axial wrap angle design step includes: and the blade outlet section obtains a plurality of target points along the current axial direction, and obtains the wrap angle optimal value corresponding to each target point. Taking one of the target points as an initial target point, and taking the optimal value of the wrap angle corresponding to the initial target point as a design value of the wrap angle. Sequentially determining the wrap angle design values of other target points along the distance from the initial target point, wherein when the wrap angle optimal value of the current target point is larger than the wrap angle design value of the previous target point and exceeds a preset value, the wrap angle design value of the current target point is the sum of the wrap angle design value of the previous target point and the preset value; when the optimal value of the wrap angle of the current target point is smaller than or equal to the design value of the wrap angle of the previous target point and exceeds a preset value, the design value of the wrap angle of the current target point is the difference between the design value of the wrap angle of the previous target point and the preset value; when the difference value between the wrap angle optimal value of the current target point and the wrap angle design value of the previous target point is smaller than a preset value, the wrap angle design value of the current target point is the wrap angle optimal value of the current target point.
According to the turbine blade design method, the wrap angle optimization control in each axial direction is carried out on the blade outlet section according to the requirement of the flow field, meanwhile, when the difference value of the change of the wrap angles exceeds the preset position, the difference value of the adjacent wrap angles is taken as the preset value to serve as the wrap angle value on the corresponding layer of the blade, and the condition that the larger stress is caused by too large change of the degree, so that the reliability is influenced, is avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present invention, and that other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
FIG. 1 is a graph of a conventional turbine blade wrap angle profile;
FIG. 2 is a schematic view of a turbine blade wrap angle provided by an embodiment of the present invention;
FIG. 3 is a graph of the internal relative velocity profile of a conventional turbine blade;
FIG. 4 is a graph of the internal relative velocity profile of a turbine blade according to an embodiment of the present invention.
Detailed Description
The core of the invention is to provide a turbine blade design method. It is a further object of the present invention to provide a turbine blade, a turbine blade design apparatus.
The present invention will be described in further detail below with reference to the drawings and embodiments, so that those skilled in the art can better understand the technical solutions of the present invention.
In order to facilitate the understanding of the scheme, the wrap angle is explained, wherein the connecting line of the front edge point of the central line of the hub and the center of the circle is a 0-degree line, the included angle between the connecting line of the rest points on the blade and the center of the circle and the 0-degree line is defined as the wrap angle, the wrap angle is positive number if the wrap angle is the same as the rotation direction of the impeller, and the wrap angle is negative number if the wrap angle is opposite to the rotation direction of the impeller.
In a specific implementation manner, the turbine blade design method provided by the specific embodiment of the invention comprises the step of designing the blade outlet section along the axial wrap angle, wherein the step of designing the blade outlet section along the axial wrap angle comprises the following steps:
and the blade outlet section obtains a plurality of target points along the current axial direction, and obtains the wrap angle optimal value corresponding to each target point. Wherein the calculation of the optimum value of the wrap angle is according to the conventional method or, in a specific calculation method: the calculating of the wrap angle optimal value comprises the following steps:
acquiring the impeller speed U on a turbine blade target point;
acquiring the absolute speed C of the air flow on a target point of the turbine blade;
calculating a relative velocity flow angle β, β=arctan (U/C) at the turbine blade target point;
calculating an optimal value alpha of the wrap angle, wherein theta=arctan (R×dα/dm), wherein theta is the blade angle on the target point, R is the radius of the impeller, and m is the length of projection of the preset position of the blade on the meridian plane. Wherein, R represents a circular arc length, which can be approximated as a straight line. Where d represents the derivative.
When calculated, β=θ, i.e., the blade angle at the target point is considered equal to the relative velocity flow angle.
As shown in fig. 3 and 4, the loss of kinetic energy at the outlet is minimized when the absolute velocity of the air flow C is minimized, wherein the arrows in the figures indicate the velocity direction.
Taking one of the target points as an initial target point, and taking the optimal value of the wrap angle corresponding to the initial target point as a design value of the wrap angle. Specifically, the initial target point may be any target point in the current axial direction, and considering that the position of the blade outlet section close to the shroud has a great influence on the airflow, it is preferable that the initial target point is the first target point of the blade outlet section close to the shroud.
Sequentially determining the wrap angle design values of other target points along the distance from the initial target point, wherein when the wrap angle optimal value of the current target point is larger than the wrap angle design value of the previous target point and exceeds a preset value, the wrap angle design value of the current target point is the sum of the wrap angle design value of the previous target point and the preset value; when the optimal value of the wrap angle of the current target point is smaller than or equal to the design value of the wrap angle of the previous target point and exceeds a preset value, the design value of the wrap angle of the current target point is the difference between the design value of the wrap angle of the previous target point and the preset value; when the difference value between the wrap angle optimal value of the current target point and the wrap angle design value of the previous target point is smaller than a preset value, the wrap angle design value of the current target point is the wrap angle optimal value of the current target point.
Specifically, the preset value is 8-12 degrees. Preferably, the preset value is 10 °. Of course, the preset value may also be less than 8 °, or greater than 12 °, in a specific design.
Preferably, the distance between two adjacent target points is equal.
From the foregoing, it will be appreciated that in the turbine blade design methods provided by the specific embodiments of the present application. According to the method, in FIG. 2, the wrap angle value of the blade outlet section in the axial direction is set to be changed, specifically, the wrap angle of the blade outlet section in each axial direction is optimally controlled according to the requirement of a flow field, and meanwhile when the difference value of the change of the wrap angle exceeds a preset position, the difference value of the change of the wrap angle and the adjacent wrap angle is used as a wrap angle value on a corresponding layer of the blade, and the problem that the change of the degree is too large to cause a larger stress is avoided, so that the reliability is influenced is solved.
The turbine blade design method comprises the steps of sequentially calculating wrap angles of multiple axial directions of the blade outlet section, and preferably, the distances between two adjacent target axes on the same blade outlet section are equal.
Each turbine blade has the same structure and is uniformly distributed along the circumferential direction.
The wrap angles are linearly distributed along the radial direction along the same axial direction of the meridian passage coordinate system.
In another embodiment, the wrap angles are distributed along the meridian passage coordinate system along the same axial direction in a quadratic curve along the radial direction.
The application provides a turbine blade design equipment, including data acquisition module and cornerite value module.
The data acquisition module is used for acquiring the wrap angle optimal value corresponding to each target point.
The wrap angle value module is configured to take one of the target points as an initial target point, where an optimal value of the wrap angle corresponding to the initial target point is taken as a wrap angle design value, specifically, the initial target point may be any target point in a current axis direction, and considering that the influence of the position of the blade outlet section close to the wheel cover on the airflow is greater, preferably, the initial target point is the first target point of the blade outlet section close to the wheel cover.
Specifically, the wrap angle design values of other target points are sequentially determined along the distance from the initial target point, when the wrap angle optimal value of the current target point is larger than the wrap angle design value of the previous target point and exceeds a preset value, the wrap angle design value of the current target point is the sum of the wrap angle design value of the previous target point and the preset value; when the optimal value of the wrap angle of the current target point is smaller than or equal to the design value of the wrap angle of the previous target point and exceeds a preset value, the design value of the wrap angle of the current target point is the difference between the design value of the wrap angle of the previous target point and the preset value; when the difference value between the wrap angle optimal value of the current target point and the wrap angle design value of the previous target point is smaller than a preset value, the wrap angle design value of the current target point is the wrap angle optimal value of the current target point. Specifically, the preset value is 8-12 degrees. Preferably, the preset value is 10 °. Of course, the preset value may also be less than 8 °, or greater than 12 °, in a specific design.
The turbine blade design equipment further comprises a wrap angle calculation module, wherein the wrap angle calculation module is used for calculating a wrap angle optimal value, and the wrap angle calculation module obtains the impeller speed U on a turbine blade target point; acquiring the speed C of the airflow on the target point of the turbine blade in the meridian plane direction; calculating a relative velocity flow angle β, β=arctan (U/C) at the turbine blade target point; calculating an optimal value alpha of the wrap angle, wherein theta=arctan (R×dα/dm), wherein theta is the blade angle on the target point, R is the radius of the impeller, and m is the length of projection of the preset position of the blade on the meridian plane. Wherein, R represents a circular arc length, which can be approximated as a straight line. Where d represents the derivative.
When calculated, β=θ, i.e., the blade angle at the target point is considered equal to the relative velocity flow angle.
Each turbine blade has the same structure and is uniformly distributed along the circumferential direction.
The wrap angles are linearly distributed along the radial direction along the same axial direction of the meridian passage coordinate system. In another embodiment, the wrap angles are distributed along the meridian passage coordinate system along the same axial direction in a quadratic curve along the radial direction.
The application provides a turbine blade, wherein the turbine blade is obtained by any one of the turbine blade design methods.
The application provides a turbine, wherein turbine blades of the turbine are obtained by any one of the turbine blade design methods. Preferably, each turbine blade on the turbine is identical in structure.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (11)
1. A method of designing a turbine blade, comprising the step of designing an axial wrap angle of an outlet section of the blade, the step of designing the axial wrap angle of the outlet section of the blade comprising:
the blade outlet section obtains a plurality of target points along the current axial direction, and obtains wrap angle optimal values corresponding to the target points;
taking one of the target points as an initial target point, and taking a wrap angle optimal value corresponding to the initial target point as a wrap angle design value;
sequentially determining the wrap angle design values of other target points along the distance from the initial target point, wherein when the wrap angle optimal value of the current target point is larger than the wrap angle design value of the previous target point and exceeds a preset value, the wrap angle design value of the current target point is the sum of the wrap angle design value of the previous target point and the preset value; when the optimal value of the wrap angle of the current target point is smaller than or equal to the design value of the wrap angle of the previous target point and exceeds a preset value, the design value of the wrap angle of the current target point is the difference between the design value of the wrap angle of the previous target point and the preset value; and when the difference value between the wrap angle optimal value of the current target point and the wrap angle design value of the previous target point is smaller than the preset value, the wrap angle design value of the current target point is the wrap angle optimal value of the current target point.
2. The turbine blade design method of claim 1, comprising sequentially calculating a plurality of said blade outlet sections along an axial wrap angle.
3. The turbine blade design method of claim 1, wherein the spacing of adjacent two of the target points is equal.
4. The turbine blade design method of claim 1, wherein calculating the wrap angle optimum value comprises the steps of:
acquiring the impeller speed U on a turbine blade target point;
acquiring the speed C of the airflow on the target point of the turbine blade in the meridian plane direction;
calculating a relative velocity flow angle β, β=arctan (U/C) at the turbine blade target point;
calculating an optimal value alpha of the wrap angle, wherein theta=arctan (R x dα/dm), wherein theta is the blade angle on the target point, R is the radius of the impeller, d is the derivative, m is the projection length of the preset position of the turbine blade on the meridian plane, and beta=theta.
5. The turbine blade design method of claim 1, wherein the spacing of adjacent target axes on the same blade outlet section is equal.
6. The turbine blade design method of claim 1, wherein the initial target point is a first target point of the blade exit section near the shroud location.
7. The turbine blade design method of claim 1, wherein the preset value is 8 ° -12 °.
8. A turbine blade designing apparatus, comprising:
the data acquisition module is used for acquiring wrap angle optimal values corresponding to all target points;
the wrap angle value module is used for taking one of the target points as an initial target point, and the wrap angle optimal value corresponding to the initial target point is taken as a wrap angle design value; sequentially determining the wrap angle design values of other target points along the distance from the initial target point, wherein when the wrap angle optimal value of the current target point is larger than the wrap angle design value of the previous target point and exceeds a preset value, the wrap angle design value of the current target point is the sum of the wrap angle design value of the previous target point and the preset value; when the optimal value of the wrap angle of the current target point is smaller than or equal to the design value of the wrap angle of the previous target point and exceeds a preset value, the design value of the wrap angle of the current target point is the difference between the design value of the wrap angle of the previous target point and the preset value; and when the difference value between the wrap angle optimal value of the current target point and the wrap angle design value of the previous target point is smaller than the preset value, the wrap angle design value of the current target point is the wrap angle optimal value of the current target point.
9. The turbine blade designing apparatus according to claim 8, further comprising a wrap angle calculation module for calculating a wrap angle optimum value, the wrap angle calculation module obtaining an impeller speed U at a turbine blade target point; acquiring the speed C of the airflow on the target point of the turbine blade in the meridian plane direction; calculating a relative velocity flow angle β, β=arctan (U/C) at the turbine blade target point; calculating an optimal value alpha of the wrap angle, wherein theta=arctan (R×dα/dm), wherein theta is the arc length of the angle corresponding to beta, R is the radius of the impeller, m is the projection length of the preset position of the blade on the meridian plane, and beta=theta.
10. A turbine blade obtained by the turbine blade design method as claimed in any one of claims 1 to 7.
11. A turbine, characterized in that turbine blades of the turbine are obtained by the turbine blade design method as claimed in any one of claims 1 to 7.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105715581A (en) * | 2016-01-26 | 2016-06-29 | 江苏大学 | Method for designing cylindrical blades of centrifugal pump |
| WO2017140756A1 (en) * | 2016-02-17 | 2017-08-24 | Volkswagen Aktiengesellschaft | Mixed-flow turbine wheel of a turbocharger, and exhaust gas turbine comprising a turbine wheel of said type |
| CN109578323A (en) * | 2018-11-07 | 2019-04-05 | 安徽工程大学 | A kind of design method of impeller vane of centrifugal pumps cornerite |
| CN113339267A (en) * | 2021-06-17 | 2021-09-03 | 清华大学 | Cambered high-energy-density blade design method and vane pump designed by same |
| CN115098966A (en) * | 2022-06-29 | 2022-09-23 | 中国航发湖南动力机械研究所 | Power turbine blade of turboprop engine and design method thereof |
-
2023
- 2023-03-17 CN CN202310260281.3A patent/CN116090137B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105715581A (en) * | 2016-01-26 | 2016-06-29 | 江苏大学 | Method for designing cylindrical blades of centrifugal pump |
| WO2017140756A1 (en) * | 2016-02-17 | 2017-08-24 | Volkswagen Aktiengesellschaft | Mixed-flow turbine wheel of a turbocharger, and exhaust gas turbine comprising a turbine wheel of said type |
| CN109578323A (en) * | 2018-11-07 | 2019-04-05 | 安徽工程大学 | A kind of design method of impeller vane of centrifugal pumps cornerite |
| CN113339267A (en) * | 2021-06-17 | 2021-09-03 | 清华大学 | Cambered high-energy-density blade design method and vane pump designed by same |
| CN115098966A (en) * | 2022-06-29 | 2022-09-23 | 中国航发湖南动力机械研究所 | Power turbine blade of turboprop engine and design method thereof |
Non-Patent Citations (2)
| Title |
|---|
| 刘磊 等: "叶片包角对离心泵水力性能影响的研究", 《水泵技术》, no. 01, pages 6 - 10 * |
| 杨军虎 等: "确定离心泵叶片包角的新方法", 《兰州理工大学学报》, vol. 36, no. 04, pages 48 - 51 * |
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