CN114060102A - Method and device for determining outlet metal angle of guide vane blade - Google Patents
Method and device for determining outlet metal angle of guide vane blade Download PDFInfo
- Publication number
- CN114060102A CN114060102A CN202111324606.7A CN202111324606A CN114060102A CN 114060102 A CN114060102 A CN 114060102A CN 202111324606 A CN202111324606 A CN 202111324606A CN 114060102 A CN114060102 A CN 114060102A
- Authority
- CN
- China
- Prior art keywords
- guide vane
- vane blade
- metal angle
- free turbine
- turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
-
- 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
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- Computer Hardware Design (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Evolutionary Computation (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Algebra (AREA)
- Computing Systems (AREA)
- Fluid Mechanics (AREA)
- Mathematical Physics (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
Abstract
A method and apparatus for exit metal angle determination of a guide vane blade for a power plant having a gas turbine and a free turbine having the guide vane blade, the method comprising: determining a target power coefficient of the free turbine based on a power matching relationship of the gas turbine and the free turbine; determining an exit metal angle of the guide vane blade based on a target power coefficient of the free turbine. Compared with the traditional scheme of adjusting the installation angle, the method can avoid the internal flow loss of the free turbine from being greatly improved, so that the efficient matching of the output power of the gas turbine and the free turbine can be realized under the condition of keeping the aerodynamic efficiency of the whole-stage turbine.
Description
Technical Field
The disclosure belongs to the technical field of internal flow hydrodynamics, and particularly relates to a method for determining an outlet metal angle of a guide vane blade, a free turbine and an engine.
Background
For a turboprop engine, a turbine part is an important source of supercharging power of a compressor and propeller thrust, and the pneumatic design of the turbine part greatly influences the pneumatic performance of the whole turboprop engine.
Due to the structural particularity of the turboprop engine, the output power of a gas turbine and the output power of a free turbine of the turboprop engine respectively meet the supercharging requirement of a gas compressor and the thrust requirement of a propeller. In the prior art, a method for adjusting the inter-stage power of a turbine is realized by adjusting the installation angle of a guide vane of a free turbine, however, in the process of adjusting the installation angle of the guide vane of the free turbine, a relatively serious aerodynamic loss is generated inside the free turbine, namely, a good inter-stage power matching effect is obtained by sacrificing certain turbine aerodynamic efficiency.
Disclosure of Invention
In order to solve the technical problem, the proper outlet metal angle of the guide vane blade is finally adjusted through the power matching relation between the gas turbine and the free turbine, and the adjusted free turbine guide vane can effectively realize the output power matching design of the gas turbine and the free turbine on the premise of keeping the output power of the whole stage of turbine.
In a first aspect, the present disclosure provides a method of exit metal angle determination for a vane blade for a power plant having a gas turbine and a free turbine, the free turbine having the vane blade, the method comprising:
determining a target power coefficient of the free turbine based on a power matching relationship of the gas turbine and the free turbine;
determining an exit metal angle of the guide vane blade based on a target power coefficient of the free turbine.
Optionally, the determining an exit metal angle of the vane blade based on the target power coefficient of the free turbine comprises:
determining an exit metal angle of the guide vane blade when the guide vane blade exit metal angle matches a target power coefficient of the free turbine;
and when the outlet metal angle of the guide vane blade is not matched with the target power coefficient of the free turbine, regulating and controlling the outlet metal angle of the guide vane blade.
Optionally, when the actual power coefficient of the free turbine is greater than the target power coefficient of the free turbine, the outlet metal angle of the guide vane blade before regulation is greater than the outlet metal angle of the guide vane blade after regulation.
Optionally, when the actual power coefficient of the free turbine is smaller than the target power coefficient of the free turbine, the outlet metal angle of the guide vane blade before regulation is smaller than the outlet metal angle of the guide vane blade after regulation.
Optionally, the adjusting the metal outlet angle of the guide vane blade comprises:
and regulating and controlling the metal angle of the outlet of the guide vane by utilizing the stacking line of the guide vane blade.
Optionally, the parameters of the vane blade include mean camber line, thickness distribution and stacking line corresponding to the mean camber line;
the stacking lines of the guide vane blades are subjected to parametric fitting by adopting curves and/or straight lines.
Optionally, before determining the exit metal angle of the guide vane blade based on the target power coefficient of the free turbine, the method further comprises:
determining a plurality of elementary profile sections distributed in the spanwise direction along the guide vane blade based on the guide vane blade,
determining a mean camber line of the elementary profile and a thickness distribution along the mean camber line based on each of the guide vane blade elementary profile sections;
parameterizing the guide vane blade based on the mean camber line and the thickness distribution of the plurality of elementary blade profiles.
Optionally, the stacking lines of the guide vane blade, the mean camber lines and the thickness distribution of the elementary airfoil are parameterized with bezier curves.
Optionally, the inlet metal angles of the guide vane blade before and after the outlet metal angle of the guide vane blade is adjusted are the same.
In a second aspect, the present disclosure also provides an exit metal angle determination apparatus of a guide vane blade, including:
a first determination module configured to determine a target power coefficient of the free turbine based on a power matching relationship of the gas turbine and the free turbine;
a second determination module connected with the first determination module and configured to determine an outlet metal angle of the guide vane blade based on a target power coefficient of the free turbine
According to one or more technical schemes provided by the disclosure, on the basis of determining a target power coefficient of the free turbine based on a power matching relation between the turboprop engine and the free turbine, an outlet metal angle of the guide vane blade is determined based on the target power coefficient of the free turbine, so that through-flow rate and an outlet flow field form inside the free turbine are changed, and output power of the free turbine and a gas turbine is adjusted. Meanwhile, compared with the traditional scheme of adjusting the installation angle, the method for adjusting and controlling the metal angle of the outlet of the free turbine can avoid the internal flow loss of the free turbine from being greatly improved, so that the efficient matching of the output power of the gas turbine and the output power of the free turbine can be realized under the condition of keeping the aerodynamic efficiency of the whole-stage turbine.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.
FIG. 1 is a graph of turbine power as a function of free turbine vane exit metal angle according to some embodiments of the present disclosure;
FIG. 2 is a schematic illustration of adjustment of a free turbine vane exit angle according to some embodiments of the present disclosure;
FIG. 3 is a schematic diagram of a method of Bezier curve parameterization according to some embodiments of the present disclosure;
FIG. 4 is a schematic adjustment diagram of adjusting the exit metal angle trailing lobe angle according to some embodiments of the present disclosure;
FIG. 5 is a comparative plot of the effect of turbine aerodynamic efficiency, according to some embodiments of the present disclosure;
FIG. 6 is a schematic structural view of an exit metal angle determining device of a vane blade according to some embodiments of the present disclosure;
Detailed Description
The present disclosure will be described in further detail with reference to the drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
In order to analyze the influence of the flow capacity of the free Turbine guide vane on the Power matching between the Turbine stages, as shown in fig. 1, the total Power of the whole stage Turbine under different free Turbine (Power Turbine) guide vane outlet metal angles and the variation trend of the output Power of the gas Turbine and the free Turbine are compared. The total output power of the whole-stage Turbine hardly changes along with the change of the metal angle of the guide vane outlet of the free Turbine, the output power of the Gas Turbine (Gas Turbine) decreases along with the increase of the metal angle of the guide vane outlet of the free Turbine, and the output power of the free Turbine increases along with the increase of the metal angle of the guide vane outlet of the free Turbine, so that the output power matching design of the Gas Turbine and the free Turbine can be effectively realized on the premise of keeping the output power of the whole-stage Turbine by adjusting the metal angle of the guide vane outlet of the free Turbine.
Based on the above analysis, the embodiment of the present disclosure provides a method for determining an outlet metal angle of a guide vane blade, in which an inlet metal angle of the guide vane and a reference length from a leading edge to a trailing edge of the blade are kept constant, and a vane installation angle is also adjusted in a linkage manner while adjusting the outlet metal angle, so as to change a throat area of the guide vane, that is, a flow area, and adjust the outlet angle of the guide vane mainly, and adjust the vane installation angle in a linkage manner secondarily, that is, to adjust a flow capacity of a turbine component, and meanwhile, compared with a conventional manner of adjusting the installation angle of the guide vane of a free turbine, the adjusting and controlling manner can effectively reduce an extra aerodynamic loss caused by adjustment and control in the free turbine.
Referring to fig. 2, an exemplary embodiment of the present disclosure provides an outlet metal angle determination method for a guide vane blade, which is used for a power plant having a gas turbine and a free turbine having the guide vane blade, including:
step S100: determining a target power coefficient of the free turbine based on a power matching relationship of the gas turbine and the free turbine; the output power of the gas turbine and the output power of the free turbine respectively meet the supercharging requirement of the gas compressor and the thrust requirement of the propeller, and a power matching relation can be obtained under the condition that the requirements are met, and the power matching relation can also be a matching relation preset according to the working conditions of the gas turbine and the free turbine according to experience. Generally, after power matching, the free turbine power coefficient and the gas turbine power coefficient are required to be able to distribute the total output power of the system substantially equally. For example, the target power coefficient of the free turbine may be 0.5, 0.49, 0.48, etc. of the total output power.
Step S200: determining an exit metal angle of the guide vane blade based on a target power coefficient of the free turbine; as shown in FIG. 1, the total power of the whole stage turbine under different free turbine guide vane exit metal angles and the trend of the output power of the gas turbine and the free turbine are compared. The total output power of the whole-stage turbine hardly changes along with the change of the metal angle of the outlet of the guide vane of the free turbine, the output power of the gas turbine decreases along with the increase of the metal angle of the outlet of the guide vane of the free turbine, and the output power of the free turbine increases along with the increase of the metal angle of the outlet of the guide vane of the free turbine, so that the matching design of the output power of the gas turbine and the output power of the free turbine can be effectively realized on the premise of keeping the output power of the whole-stage turbine by adjusting the metal angle of the outlet of the guide vane of the free turbine. After determining the target power coefficient of the free turbine, the outlet metal angle of the guide vane blade may be adjusted with the target power coefficient of the free turbine as a target until an outlet metal angle satisfying a power matching relationship of the gas turbine and the free turbine is obtained.
In order to analyze the effect of the outlet metal angles of the adjusting guide vane blades on the power matching between the turbine stages, as shown in fig. 1, the total power of the whole stage turbine at different outlet metal angles of the free turbine guide vanes and the variation trend of the output power of the gas turbine and the free turbine are compared. The total output power of the whole-stage turbine hardly changes along with the change of the metal angle of the outlet of the guide vane of the free turbine, the output power of the gas turbine decreases along with the increase of the metal angle of the outlet of the guide vane of the free turbine, and the output power of the free turbine increases along with the increase of the metal angle of the outlet of the guide vane of the free turbine, so that the output power matching of the gas turbine and the free turbine can be effectively realized on the premise of keeping the output power of the whole-stage turbine by adjusting the metal angle of the outlet of the guide vane of the free turbine.
In a possible implementation manner, in step S200, the method for specifically determining the metal outlet angle includes:
when the outlet metal angle of the guide vane blade is not matched with the target power coefficient of the free turbine, regulating and controlling the outlet metal angle of the guide vane blade; the outlet metal angle is regulated and controlled by the method until the outlet metal angle is matched with the target power coefficient of the free turbine, and the regulation and control method can be realized by a computer simulation regulation and control method, so that the operation speed is high.
Determining an outlet metal angle of a guide vane blade by regulating and controlling the outlet metal angle of the guide vane blade for a plurality of times until the outlet metal angle of the guide vane blade is matched with a target power coefficient of the free turbine; thereby achieving the optimal outlet metal angle.
Referring to fig. 1, according to a graph of a change of turbine power along with a free turbine guide vane outlet metal angle, in step S200, a specific manner of regulating the outlet metal angle is that, when an actual power coefficient of the free turbine is smaller than a target power coefficient of the free turbine, the outlet metal angle before regulation of the guide vane blade is smaller than the outlet metal angle after regulation of the guide vane blade, in order to increase the free turbine power coefficient, the outlet metal angle of the guide vane blade is increased, then the free turbine power coefficient is recalculated, and whether matching is performed is determined; when the actual power coefficient of the free turbine is larger than the target power coefficient of the free turbine, the outlet metal angle before the regulation and control of the guide vane blade is larger than the outlet metal angle after the regulation and control of the guide vane blade, the outlet metal angle of the guide vane blade is reduced in order to reduce the power coefficient of the free turbine, the power coefficient of the free turbine is recalculated, and whether the free turbine is matched or not is judged.
In a preferred embodiment, the outlet metal angle of the guide vane blade can be regulated and controlled by adopting a three-dimensional blade modeling software analysis method, and the parameters of the guide vane blade comprise a mean camber line, thickness distribution and stacking lines corresponding to the mean camber line; the stacking lines of the guide vane blades are subjected to parametric fitting by adopting curves and/or straight lines.
For example, Autoblade parameterization software can be used for analysis, the free turbine guide vane blade is geometrically parameterized firstly, and the guide vane outlet metal angle is regulated and controlled in the software by changing the parameters of the guide vane blade curve.
In another embodiment, before the step 200, a geometric parameterization of the entire guide vane blade is further performed, specifically including:
a step S191 of determining, based on the guide vane blade, a plurality of elementary profile sections distributed in the spanwise direction along the guide vane blade; for example, a free turbine vane may be illustratively spanwise divided into 21 elementary airfoil sections. The division of 30, 35 and 40 primitive blade profile sections also does not affect the implementation of the present disclosure, and the more primitive blade profile sections, the more accurate the parameterization result.
Step S192, determining a mean camber line of the elementary profile and a thickness distribution along the mean camber line based on each of the guide vane blade elementary profile sections; for example, referring to fig. 3, the elementary leaf profile cross section may be parameterized and fitted by introducing Autoblade parameterization software to the mean camber line 1 and the thickness distribution of each elementary leaf profile by using a curve and/or a straight line; in the present embodiment, the parameterization is performed by using a Bezier curve (Simple Bezier curve), and the integral line of the elementary leaf profile is parameterized and fitted by using a continuous Bezier curve, a straight line and a Bezier curve (Bezier-line-Bezier curve). For another example, the mean camber line 1 or the stacking line may also be a parameterized result that simulates the mean camber line 1 and the thickness distribution using one or more of a straight line, a circular arc, and a spline curve.
Step S193, parameterizing the guide vane blade based on the mean camber line and the thickness distribution of the plurality of primitive blade profiles. And finally, stacking each element blade profile in the Autoblade parameterization software along the gravity center to obtain a geometric parameterization result, so that the geometric parameterization of the whole guide vane blade is realized.
Referring to fig. 3 and 4, when parameterizing the geometry of the guide vane blade, the camber line 1 mainly has three control angles, which are an inlet metal angle β 1, an outlet metal angle β 2, and a vane profile installation angle γ. In the regulation and control process, the throat area and the through-flow capacity of the guide vane blade of the free turbine are changed by regulating the guide vane outlet metal angle beta 2, so that the matching design of the output power of the gas turbine and the free turbine is realized.
The method for adjusting the outlet metal angle in the parameterized software comprises the following steps: the metal angle of the outlet of the guide vane can be regulated and controlled by utilizing the stacking line of the guide vane blade; in the embodiment, the regulation and control of the metal angle beta 2 of the outlet of the guide vane is realized by changing the parameters of the local Simple Bezier curve of the vane, and meanwhile, other geometric parameters of each element vane profile are kept unchanged.
In another embodiment, in step S200, in order to prevent the total output power of the entire turbine from varying, the outlet metal angle β 2 of the guide vane blade is kept constant, that is, the inlet metal angle of the guide vane blade before and after the outlet metal angle of the guide vane blade is adjusted is the same. Referring to FIG. 5, as the turbine vane setting angle changes, the vane area increases or decreases, both of which result in a decrease in turbine efficiency; by adjusting the outlet metal angle beta 2, the total efficiency of the turbine is relatively small in change.
This disclosure adjusts the free turbine guide vane: the metal angle of the inlet of the guide vane is kept unchanged, the throat area of the blade channel is changed by adjusting the metal angle of the outlet of the guide vane, namely the through-flow capacity of the turbine component is adjusted, and meanwhile, as shown in figure 5, compared with the traditional mode of adjusting the installation angle of the guide vane of the free turbine, the adjusting and controlling mode can effectively reduce extra aerodynamic loss caused by adjustment and control in the free turbine.
Referring to fig. 6, the present disclosure also provides an outlet metal angle determining apparatus of a guide vane blade, including:
a first determination module 2 configured to determine a target power coefficient of the free turbine based on a power matching relationship of the gas turbine and the free turbine;
a second determination module 3 connected to the first determination module 2, configured to determine an exit metal angle of the guide vane blade based on a target power coefficient of the free turbine.
In the present disclosure, the first determination module 2 determines a target power coefficient, and when the free turbine power coefficient satisfies the output power match of the gas turbine and the free turbine, the second determination module 3 obtains the corresponding outlet metal angle at the time of the power match. For each combination of gas turbine and free turbine, the exit metal angle of the free turbine is different when its power is matched; the matching design of output power can be realized by adjusting the inlet metal angle of the free turbine guide vane blade according to the device, and meanwhile, the power loss is small.
Embodiments of the present disclosure also provide a device for determining an exit metal angle of a free turbine on a power plant having a free turbine and a gas turbine, the device comprising a processor and a memory. Wherein the memory has stored therein computer program instructions adapted to be executed by the processor. When the computer program instructions are executed by a processor, the processor executes the exit metal angle determination apparatus provided in any of the above embodiments.
It should be noted that, when the outlet metal angle determining device for the guide vane blade provided in the above embodiment is used to determine the outlet metal angle, the division of the above functional modules is merely exemplified, and in practical applications, the above function distribution may be completed by different functional modules according to needs, that is, the internal structure or program of the device is divided into different functional modules to complete all or part of the above described functions. In addition, the outlet metal angle embodiments provided by the above embodiments belong to the same concept, and specific implementation processes thereof are described in method embodiments for details, which are not described herein again.
The embodiments of the present disclosure also provide a computer-readable storage medium, in which computer program instructions are stored, and when the computer program instructions are executed by a processor of a user equipment, the user equipment is caused to execute the method disclosed in any of the above embodiments.
Computer-readable storage media provided by any embodiment of the present disclosure include permanent and non-permanent, removable and non-removable media, and information storage may be implemented by any method or technology. The information may be computer readable instructions, data structures, modules of a program, or other data. Examples of computer storage media include, but are not limited to, phase change memory (PRAM), Static Random Access Memory (SRAM), Dynamic Random Access Memory (DRAM), other types of Random Access Memory (RAM), Read Only Memory (ROM), Electrically Erasable Programmable Read Only Memory (EEPROM), flash memory or other memory technology, compact disc read only memory (CD-ROM), Digital Versatile Discs (DVD) or other optical storage, magnetic cassettes, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other non-transmission medium that can be used to store information that can be accessed by a computing device.
The embodiment of the present disclosure further provides an electronic device, which includes a processor and a memory, where the memory stores computer program instructions suitable for the processor to execute, and the computer program instructions are executed by the processor to perform the method disclosed in any of the above embodiments.
The electronic device provided by any embodiment of the present disclosure may be a mobile phone, a computer, a tablet computer, a server, a network device, or may also be a usb disk, a removable hard disk, a Read Only Memory (ROM), a magnetic disk, or an optical disk.
For example, the electronic device may include: a processor, a memory, an input/output interface, a communication interface, and a bus. Wherein the processor, the memory, the input/output interface and the communication interface are communicatively connected to each other within the device by a bus.
The processor may be implemented by a general-purpose CPU (Central Processing Unit), a microprocessor, an Application Specific Integrated Circuit (ASIC), or one or more Integrated circuits, and is configured to execute a relevant program to implement the technical solutions provided in the embodiments of the present specification.
The Memory may be implemented in the form of a ROM (Read Only Memory), a RAM (Random Access Memory), a static storage device, a dynamic storage device, or the like. The memory may store an operating system and other application programs, and when the technical solution provided by the embodiments of the present specification is implemented by software or firmware, the relevant program codes are stored in the memory and called by the processor to be executed.
The input/output interface is used for connecting the input/output module to realize information input and output. The input/output/modules may be configured in the device as components or may be external to the device to provide corresponding functionality. The input devices may include a keyboard, a mouse, a touch screen, a microphone, various sensors, etc., and the output devices may include a display, a speaker, a vibrator, an indicator light, etc.
The communication interface is used for connecting the communication module so as to realize the communication interaction between the equipment and other equipment. The communication module can realize communication in a wired mode (such as USB, network cable and the like) and also can realize communication in a wireless mode (such as mobile network, WIFI, Bluetooth and the like).
A bus includes a path that transfers information between the various components of the device, such as the processor, memory, input/output interfaces, and communication interfaces.
It should be noted that although the above-described device shows only a processor, a memory, an input/output interface, a communication interface and a bus, in a specific implementation, the device may also include other components necessary for normal operation. In addition, those skilled in the art will appreciate that the above-described apparatus may also include only the components necessary to implement the embodiments of the present description, and not necessarily all of the described components.
From the above description of the embodiments, it is clear to those skilled in the art that the embodiments of the present disclosure can be implemented by software plus necessary general hardware platform. Based on such understanding, the technical solutions of the embodiments of the present specification may be essentially or partially implemented in the form of a software product, which may be stored in a storage medium, such as a ROM/RAM, a magnetic disk, an optical disk, etc., and includes several instructions for enabling a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the methods described in the embodiments or some parts of the embodiments of the present specification.
The systems, methods, modules or units described in the above embodiments may be implemented by a computer chip or an entity, or by a product with certain functions. A typical implementation device is a computer, which may take the form of a personal computer, laptop computer, cellular telephone, camera phone, smart phone, personal digital assistant, media player, navigation device, email messaging device, game console, tablet computer, wearable device, or a combination of any of these devices.
In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
It will be understood by those skilled in the art that the foregoing embodiments are merely for clarity of illustration of the disclosure and are not intended to limit the scope of the disclosure. Other variations or modifications may occur to those skilled in the art, based on the foregoing disclosure, and are still within the scope of the present disclosure.
Claims (10)
1. A method of exit metal angle determination for a vane blade for a power plant having a gas turbine and a free turbine, the free turbine having the vane blade, the method comprising:
determining a target power coefficient of the free turbine based on a power matching relationship of the gas turbine and the free turbine;
determining an exit metal angle of the guide vane blade based on a target power coefficient of the free turbine.
2. The exit metal angle determination method of a guide vane blade of claim 1, wherein the determining the exit metal angle of the guide vane blade based on the target power coefficient of the free turbine comprises:
determining an exit metal angle of the guide vane blade when the guide vane blade exit metal angle matches a target power coefficient of the free turbine;
and when the outlet metal angle of the guide vane blade is not matched with the target power coefficient of the free turbine, regulating and controlling the outlet metal angle of the guide vane blade.
3. The exit metal angle determination method of a guide vane blade according to claim 2,
when the actual power coefficient of the free turbine is larger than the target power coefficient of the free turbine, the outlet metal angle of the guide vane blade before regulation is larger than the outlet metal angle of the guide vane blade after regulation.
4. The exit metal angle determination method of a guide vane blade according to claim 2,
when the actual power coefficient of the free turbine is smaller than the target power coefficient of the free turbine, the outlet metal angle of the guide vane blade before regulation is smaller than the outlet metal angle of the guide vane blade after regulation.
5. The exit metal angle determination method of a guide vane blade according to claim 2, characterized in that: the pair the stator blade outlet metal angle is regulated and controlled, including:
and regulating and controlling the metal angle of the outlet of the guide vane by utilizing the stacking line of the guide vane blade.
6. The exit metal angle determination method of a guide vane blade according to claim 1,
the parameters of the guide vane blade comprise a mean camber line, a thickness distribution and an integral line corresponding to the mean camber line;
the stacking lines of the guide vane blades are subjected to parametric fitting by adopting curves and/or straight lines.
7. The exit metal angle determination method of a guide vane blade according to claim 1,
before determining an exit metal angle of the guide vane blade based on the target power coefficient of the free turbine, the method further comprises:
determining a plurality of elementary profile sections distributed in the spanwise direction along the guide vane blade based on the guide vane blade,
determining a mean camber line of the elementary profile and a thickness distribution along the mean camber line based on each of the guide vane blade elementary profile sections;
parameterizing the guide vane blade based on the mean camber line and the thickness distribution of the plurality of elementary blade profiles.
8. The exit metal angle determination method of a vane blade of claim 7, characterized by: and the stacking lines of the guide vane blade, the mean camber lines and the thickness distribution of the elementary blade profile are parameterized by a Bezier curve.
9. The exit metal angle determination method of a guide vane blade according to claim 1, characterized in that:
the inlet metal angles of the guide vane blade before and after the outlet metal angle of the guide vane blade is regulated and controlled are the same.
10. An exit metal angle determining apparatus of a guide vane blade, comprising:
a first determination module configured to determine a target power coefficient of the free turbine based on a power matching relationship of the gas turbine and the free turbine;
a second determination module connected to the first determination module configured to determine an exit metal angle of the guide vane blade based on a target power coefficient of the free turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111324606.7A CN114060102B (en) | 2021-11-10 | 2021-11-10 | Method and device for determining outlet metal angle of guide vane blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111324606.7A CN114060102B (en) | 2021-11-10 | 2021-11-10 | Method and device for determining outlet metal angle of guide vane blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114060102A true CN114060102A (en) | 2022-02-18 |
| CN114060102B CN114060102B (en) | 2022-11-04 |
Family
ID=80274512
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111324606.7A Active CN114060102B (en) | 2021-11-10 | 2021-11-10 | Method and device for determining outlet metal angle of guide vane blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114060102B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115098958A (en) * | 2022-05-29 | 2022-09-23 | 中国船舶重工集团公司第七0三研究所 | Air-cooled turbine guide vane modeling method for exhausting air at suction side |
| CN115130234A (en) * | 2022-05-29 | 2022-09-30 | 中国船舶重工集团公司第七0三研究所 | Air-cooled turbine guide vane modeling method for pressure side exhaust |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4266401A (en) * | 1977-12-22 | 1981-05-12 | The Garrett Corporation | Gas turbine engine fuel control |
| US4269027A (en) * | 1977-12-22 | 1981-05-26 | The Garrett Corporation | Gas turbine engine idle control and method |
| US4899537A (en) * | 1984-02-07 | 1990-02-13 | International Power Technology, Inc. | Steam-injected free-turbine-type gas turbine |
| US20030066294A1 (en) * | 2001-10-10 | 2003-04-10 | Giovanni Mannarino | Control system for positioning compressor inlet guide vanes |
| CN103321754A (en) * | 2013-05-27 | 2013-09-25 | 南京航空航天大学 | Helicopter/engine comprehensive simulation model and turboshaft engine control method |
| JP2018059491A (en) * | 2016-10-03 | 2018-04-12 | 根本 勇 | Flow control method of ultrahigh bypass ratio variable cycle turbofan |
| CN109614722A (en) * | 2018-12-14 | 2019-04-12 | 中国人民解放军陆军航空兵学院 | The modeling method of turboshaft engine total state parameter based on fuzzy logic |
-
2021
- 2021-11-10 CN CN202111324606.7A patent/CN114060102B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4266401A (en) * | 1977-12-22 | 1981-05-12 | The Garrett Corporation | Gas turbine engine fuel control |
| US4269027A (en) * | 1977-12-22 | 1981-05-26 | The Garrett Corporation | Gas turbine engine idle control and method |
| US4899537A (en) * | 1984-02-07 | 1990-02-13 | International Power Technology, Inc. | Steam-injected free-turbine-type gas turbine |
| US20030066294A1 (en) * | 2001-10-10 | 2003-04-10 | Giovanni Mannarino | Control system for positioning compressor inlet guide vanes |
| CN103321754A (en) * | 2013-05-27 | 2013-09-25 | 南京航空航天大学 | Helicopter/engine comprehensive simulation model and turboshaft engine control method |
| JP2018059491A (en) * | 2016-10-03 | 2018-04-12 | 根本 勇 | Flow control method of ultrahigh bypass ratio variable cycle turbofan |
| CN109614722A (en) * | 2018-12-14 | 2019-04-12 | 中国人民解放军陆军航空兵学院 | The modeling method of turboshaft engine total state parameter based on fuzzy logic |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115098958A (en) * | 2022-05-29 | 2022-09-23 | 中国船舶重工集团公司第七0三研究所 | Air-cooled turbine guide vane modeling method for exhausting air at suction side |
| CN115130234A (en) * | 2022-05-29 | 2022-09-30 | 中国船舶重工集团公司第七0三研究所 | Air-cooled turbine guide vane modeling method for pressure side exhaust |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114060102B (en) | 2022-11-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114060102B (en) | Method and device for determining outlet metal angle of guide vane blade | |
| CN110727995B (en) | Blade shape construction method, blade, and computer device | |
| CN116561934B (en) | Blade performance angle model correction method and device, electronic equipment and storage medium | |
| CN110851929A (en) | Two-dimensional leaf-type optimization design method and device based on self-adaptive grid | |
| CN116186947B (en) | Impeller simulation design method, device, equipment, medium and product | |
| CN112417773B (en) | Multidisciplinary optimization design method, device and equipment of multistage axial flow expander | |
| CN111027148B (en) | Automatic calibration and industrial axial flow compressor performance calculation method for loss lag angle model | |
| CN110647052A (en) | Variable cycle engine mode switching self-adaptive identity card model construction method | |
| JP2017062676A (en) | Ventilation analysis system for axial flow fan, ventilation analysis device and ventilation analysis program | |
| CN113033112A (en) | Method and equipment for modeling clean room air system | |
| CN116050031A (en) | Axial flow impeller blade design method and device, storage medium and electronic equipment | |
| CN116384005A (en) | Method and device for determining aerodynamic performance of deformed blade and electronic equipment | |
| CN116502372B (en) | Impeller mechanical modeling method and device, storage medium and electronic equipment | |
| CN111241653B (en) | Multi-dimensional blade error performance influence simulation implementation method based on Monte Carlo method | |
| CN108664742B (en) | Multi-objective optimization method for nacelle parametric design | |
| CN113987974B (en) | Optimization method and device for guide vane parameters | |
| CN116663168A (en) | Turbine-level working parameter determining method and device, electronic equipment and storage medium | |
| CN114692344B (en) | Wind driven generator optimization design method and system based on computer assistance | |
| CN116579252A (en) | Particle swarm optimization-based vortex mechanical exhaust hole optimization method and system | |
| CN111339609A (en) | Blade, method and device for constructing thickness distribution of blade, and computer-readable storage medium | |
| CN114429071A (en) | Hub profile optimization method and system of axial flow fan for server | |
| CN117744283B (en) | Design method, device, equipment and computer storage medium for compressor | |
| CN117763878B (en) | Method and device for determining blade profile of air compressor and storage medium | |
| Lotz | Aerodynamic Optimization Process for Turbocharger Compressor Impellers | |
| CN116502568B (en) | Method, device, equipment and medium for automatically simulating internal flow characteristics of gas compressor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |