CN117869016A - Cooling unit for reducing heat conduction of turbine outer ring and analysis method thereof - Google Patents
Cooling unit for reducing heat conduction of turbine outer ring and analysis method thereof Download PDFInfo
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Abstract
The application provides a cooling unit for reducing heat conduction of a turbine outer ring and an analysis method thereof, which belong to the technical field of aeroengines, wherein the cooling unit is arranged on the turbine outer ring and is positioned in a contact area of the turbine outer ring and a turbine casing, and a ventilation gap communicated with the cooling unit is arranged between the turbine outer ring and the turbine casing; the cooling unit is provided with a zigzag channel with a groove structure and comprises a first channel, a second channel and a third channel which are connected with each other, the opening end of the first channel is flush with the edge of one side of the axial direction of the turbine outer ring, and the opening end of the third channel is flush with the edge of the other side; the first channel axis forms a first channel included angle with the edge of the turbine outer ring, the first channel axis forms a second channel included angle with the second channel axis, the second channel axis forms a third channel included angle with the third channel axis, and the three channels have the same groove width and groove depth. According to the heat conduction device, under the condition that the force transmission between the turbine outer ring and the turbine casing is not affected, the heat conduction from the turbine outer ring to the turbine casing is effectively reduced.
Description
Technical Field
The application relates to the technical field of aeroengines, in particular to a cooling unit for reducing heat conduction of an outer ring of a turbine and an analysis method thereof.
Background
With the continuous improvement of the performance of the aero-engine and the continuous increase of the service life and reliability demands, the inlet temperature before the turbine is higher and higher, and the higher inlet temperature of the turbine brings higher requirements for the safe and efficient operation of the hot end component of the engine. Stator components corresponding to the turbine movable blades are reasonable in clearance and can prevent high-temperature fuel gas from being washed. In order to prevent the flushing of high-temperature fuel gas, a turbine outer ring is arranged on a turbine casing, the whole outer ring is generally divided into a plurality of blocks in consideration of convenient installation and thermal deformation of materials, and a special cooling flow path is designed to isolate the high-temperature fuel gas.
The scholars at home and abroad develop a great deal of theoretical research, numerical simulation and test work in the aspect of turbine outer ring cooling, and mainly concentrate on the cooling design of the turbine outer ring. On the one hand, for the single and compound modes of cooling forms such as convection, impact, air film and the like, how to improve the cooling efficiency is studied; on the other hand, for the structure and the material of the turbine outer ring, how to improve the temperature distribution uniformity and the temperature resistance level of the turbine outer ring is studied. The researches well solve the cooling problem of the turbine outer ring, but because the turbine outer ring is hung on the turbine casing, a high-temperature area is inevitably formed at a contact position, so that the development cost of the turbine casing is increased.
As known from the known data, the cooling scheme of the outer ring of the turbine, which is published in China, mainly comprises the following steps: the utility model provides a turbine outer ring and a method for arranging cooling air film holes of the turbine outer ring (CN 115506858A), and research on the flow and heat exchange characteristics of a cooling structure of a turbine outer ring block (Zhu Yuting, the university of aviation aerospace, university of Nanjing) provides a cooling method of the turbine outer ring block, but no design method and structure for reducing heat conduction from the turbine outer ring to a turbine casing are provided.
Therefore, the existing turbine outer ring cooling research has the problems that the heat conduction from the turbine outer ring to the turbine casing is large, and a heat conduction analysis method for reducing the turbine outer ring is lacking.
Disclosure of Invention
In view of this, the embodiments of the present application provide a cooling unit for reducing heat conduction of a turbine outer ring and an analysis method thereof, which are mainly used for solving the problems of large heat conduction from the turbine outer ring to a turbine casing and lack of a method for reducing heat conduction analysis of the turbine outer ring in the prior art.
In a first aspect, an embodiment of the present application provides a cooling unit for reducing heat conduction of a turbine outer ring, where the cooling unit is disposed on the turbine outer ring and is located in a contact area between the turbine outer ring and a turbine casing, and a ventilation slot is disposed between the turbine outer ring and the turbine casing, and the ventilation slot is communicated with the cooling unit, and cold air flow of the cooling unit is controlled by adjusting a slot width of the ventilation slot;
the cooling unit is provided with a plurality of zigzag channels with groove structures, the zigzag channels are arranged in the circumferential direction of the turbine outer ring, each zigzag channel comprises a first channel, a second channel and a third channel which are connected with each other, the open end of each first channel is flush with one axial side edge of the turbine outer ring, and the open end of each third channel is flush with the other axial side edge of the turbine outer ring; a first channel included angle alpha is formed between the axis of the first channel and the edge of the turbine outer ring, a second channel included angle beta is formed between the axis of the first channel and the axis of the second channel, a third channel included angle theta is formed between the axis of the second channel and the axis of the third channel, and the first channel, the second channel and the third channel have the same groove width and groove depth.
According to a specific implementation manner of the embodiment of the application, the first channel included angle α ranges from 30 ° to 60 °.
According to a specific implementation manner of the embodiment of the present application, the first channel included angle α, the second channel included angle β, and the third channel included angle θ are all the same.
According to a specific implementation manner of the embodiment of the application, the value range of the groove depth is 0.4-0.6mm.
According to a specific implementation manner of the embodiment of the application, the value of the groove width is 3-5 times of the groove depth.
According to a specific implementation manner of the embodiment of the present application, a plurality of the zigzag channels are uniformly arranged in the circumferential direction of the turbine outer ring.
In a second aspect, an embodiment of the present application further provides an analysis method of a cooling unit for reducing heat conduction of an outer ring of a turbine, where the cooling unit for reducing heat conduction of an outer ring of a turbine is used for analysis, and the method includes:
obtaining physical parameters during calculation of the two-dimensional temperature field of the zigzag channel, wherein the physical parameters comprise a mixed heat conductivity coefficient;
obtaining a heat exchange boundary of the zigzag channel during calculation of the two-dimensional temperature field, wherein the heat exchange boundary comprises a mixed heat exchange coefficient;
a two-dimensional temperature field calculation model is adopted, heat exchange boundaries comprising the mixed heat exchange coefficients are respectively loaded to the upper boundary and the lower boundary of the zigzag channel, physical property parameters comprising the mixed heat conduction coefficients are loaded to the area between the upper boundary and the lower boundary of the zigzag channel, and two-dimensional temperature field calculation is carried out;
and analyzing the temperature distribution condition of the turbine casing under the action of the cooling unit according to the two-dimensional temperature field calculation result.
According to a specific implementation manner of the embodiment of the present application, the calculation formula of the mixed thermal conductivity is:
，
wherein lambda is Mixing Lambda is the mixed thermal conductivity Empty space Is the heat conductivity coefficient lambda of the cooling air in the zigzag channel Fixing device For the thermal conductivity of the material used for the turbine outer ring, V A kind of electronic device V for the total volume of all the zigzag passages in the circumferential direction of the turbine outer ring Fixing device Is the volume of the turbine outer ring solid at the same position of the zigzag channel.
According to a specific implementation manner of the embodiment of the present application, the calculation formula of the hybrid heat exchange coefficient is:
，
wherein h is Mixing For the mixed heat exchange coefficient, h A kind of electronic device The heat exchange coefficient of the cooling air in the zigzag channel.
According to a specific implementation of the embodiment of the present application, the total volume V of all the zigzag channels in the circumferential direction of the turbine outer ring A kind of electronic device The calculation formula of (2) is as follows:
，
volume V of the turbine outer ring solid at the same position of the zigzag passage Fixing device The calculation formula of (2) is as follows:
V fixing device =2πrxL-V A kind of electronic device ，
Wherein x is the groove depth, y is the groove width, z is the first channel length, r is the radius of the contact area, and L is the turbine outer ring axial length.
Advantageous effects
According to the cooling unit for reducing heat conduction of the outer turbine ring and the analysis method thereof, the zigzag channel is arranged in the contact area of the outer turbine ring and the turbine casing, and heat conduction from the outer turbine ring to the turbine casing can be effectively reduced under the condition that force transmission between the outer turbine ring and the turbine casing is not affected. The analysis method based on the equal volume can solve the problem of lack of the analysis method for reducing the heat conduction of the outer ring of the turbine.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a cooling unit for reducing heat conduction from an outer ring of a turbine according to an embodiment of the invention;
FIG. 2 is an A-direction view of the turbine outer ring of FIG. 1;
FIG. 3 is another schematic diagram of a cooling unit for reducing heat conduction from an outer ring of a turbine according to an embodiment of the invention;
fig. 4 is a schematic diagram of a two-dimensional temperature field calculation result according to an embodiment of the present invention, (a) a calculation result without a cooling unit, and (b) a calculation result with a cooling unit.
In the figure: 1. the turbine casing, 2, the turbine outer ring, 3, the region between the upper boundary and the lower boundary, 4, the upper boundary, 5, the lower boundary.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the present disclosure, when the following description of the embodiments is taken in conjunction with the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The present application may be embodied or carried out in other specific embodiments, and the details of the present application may be modified or changed from various points of view and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concepts of the application by way of illustration, and only the components related to the application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
In a first aspect, embodiments of the present application provide a cooling unit for reducing heat conduction from an outer ring of a turbine, as described in detail below with reference to fig. 1-4.
In one embodiment, a cooling unit for reducing heat conduction of the turbine outer ring is arranged on the turbine outer ring 2 and is positioned in a contact area between the turbine outer ring 2 and the turbine casing 1, a ventilation gap is arranged between the turbine outer ring 2 and the turbine casing 1, the ventilation gap is communicated with the cooling unit, and cold air flow of the cooling unit is controlled by adjusting the gap width delta of the ventilation gap;
the cooling unit is provided with a zigzag channel with a groove structure, the zigzag channel is provided with a plurality of zigzag channels in the circumferential direction of the turbine outer ring 2, the zigzag channel comprises a first channel, a second channel and a third channel which are connected with each other, the open end of the first channel is flush with one axial side edge of the turbine outer ring 2, and the open end of the third channel is flush with the other axial side edge of the turbine outer ring 2; a first channel included angle alpha is formed between the axis of the first channel and the edge of the turbine outer ring 2, a second channel included angle beta is formed between the axis of the first channel and the axis of the second channel, a third channel included angle theta is formed between the axis of the second channel and the axis of the third channel, and the first channel, the second channel and the third channel have the same groove width and groove depth.
Specifically, referring to fig. 1 and 2, the zigzag pattern in fig. 2 is a zigzag channel, and the zigzag channel control dimensions include a groove depth x, a groove width y, a first channel length Z, a first channel included angle α, a second channel included angle β, a third channel included angle θ, and an axial length L of the turbine outer ring 2. The zigzag channels have the main functions of forming cooling channels and preventing heat from being transferred from the turbine outer ring 2 to the turbine casing 1, and meanwhile, the force transfer between the turbine outer ring 2 and the turbine casing 1 is not affected, and a plurality of groups of zigzag channels can be selected according to requirements and uniformly distributed on the turbine outer ring 2 along the circumferential direction.
Preferably, the first channel included angle α is in the range of 30 ° to 60 °.
Preferably, the first channel included angle α, the second channel included angle β, and the third channel included angle θ are all the same.
Preferably, the value range of the groove depth is 0.4-0.6mm.
Preferably, the groove width is 3-5 times of the groove depth.
And a ventilation gap between the turbine outer ring 2 and the turbine casing 1, wherein the ventilation gap is formed by a gap between the turbine outer ring 2 and the turbine casing 1, and the ventilation gap is controlled to be the seam width delta. The main function of the ventilation slit is to control the cold air flow of the zigzag channel, wherein the cold air flow can be obtained by air system characteristic calculation software according to the slit width delta.
Preferably, a plurality of the zigzag passages are uniformly arranged in the circumferential direction of the turbine outer ring 2.
In a second aspect, an embodiment of the present application further provides an analysis method for a cooling unit for reducing heat conduction of the turbine outer ring 2, where the cooling unit for reducing heat conduction of the turbine outer ring 2 as described in any one of the embodiments of the first aspect is used for analysis, and the method is a thermal analysis method, and the thermal analysis method is applicable to two-dimensional temperature field calculation, and determines physical property parameters and heat exchange boundaries of the zigzag channel mainly through an isovolumetric principle. The method comprises the following steps:
and step S101, obtaining physical parameters during calculation of the two-dimensional temperature field of the zigzag channel, wherein the physical parameters comprise a mixed heat conductivity coefficient.
Specifically, the calculation formula of the mixed heat conductivity coefficient is as follows:
，
wherein lambda is Mixing Lambda is the mixed thermal conductivity Empty space Is the heat conductivity coefficient lambda of the cooling air in the zigzag channel Fixing device For the thermal conductivity, V, of the material used for the turbine outer ring 2 A kind of electronic device V for the total volume of all the zigzag passages in the circumferential direction of the turbine outer ring 2 Fixing device Is the volume of solid of the turbine outer ring 2 at the same position of the zigzag channel.
Specifically, the total volume V of all the zigzag passages in the circumferential direction of the turbine outer ring 2 A kind of electronic device The calculation formula of (2) is as follows:
，
volume V of solid of the turbine outer ring 2 at the same position of the zigzag passage Fixing device The calculation formula of (2) is as follows:
V fixing device =2πrxL-V A kind of electronic device ，
Where x is the groove depth, y is the groove width, z is the first channel length, r is the radius of the contact area, and L is the axial length of the turbine outer ring 2.
And S102, obtaining a heat exchange boundary during calculation of the two-dimensional temperature field of the zigzag channel, wherein the heat exchange boundary comprises a mixed heat exchange coefficient.
Specifically, the calculation formula of the mixed heat exchange coefficient is as follows:
，
wherein h is Mixing For the mixed heat exchange coefficient, h A kind of electronic device The heat exchange coefficient of the cooling air in the zigzag channel.
Step S103, using a two-dimensional temperature field calculation model, referring to fig. 3, loading heat exchange boundaries including the mixed heat exchange coefficient to the upper boundary 4 and the lower boundary 5 of the zigzag channel, and loading physical parameters including the mixed heat conduction coefficient to the region 3 between the upper boundary and the lower boundary of the zigzag channel, so as to perform two-dimensional temperature field calculation.
Step S104, analyzing the temperature distribution condition of the turbine casing 1 under the action of the cooling unit according to the two-dimensional temperature field calculation result.
Further, the temperature field calculation of the turbine outer ring 2 and the turbine casing 1 is carried out, if the temperature of the turbine casing 1 is higher, the circumferential distribution quantity of zigzag channels can be increased, the angles of the first channel included angle alpha, the second channel included angle beta or the third channel included angle theta are reduced, the groove depth x, the groove width y or the slit width delta are increased, the heat conduction quantity is further reduced, and the temperature of the turbine casing 1 is reduced.
The following detailed description is provided with reference to a specific embodiment, and mainly includes the following.
The zigzag passage is a zigzag cooling air passage composed of square grooves, and is arranged on the turbine outer ring 2 at the contact area of the turbine outer ring 2 and the turbine casing 1.
For example, the zigzag channel control dimension groove depth=1.0 mm, groove width=0.4 mm, first channel length 4mm, first channel included angle α 45 °, second channel included angle β 45 °, and third channel included angle θ 45 °.
The turbine outer ring 2 and the turbine casing 1 are vented, which is formed by a gap between the turbine outer ring 2 and the turbine casing 1.
Illustratively, the vent-slit control dimension has a slit width of 0.2mm.
The analysis method of the cooling unit for reducing the heat conduction of the outer ring of the turbine adopts a thermal analysis method, the thermal analysis method is suitable for two-dimensional temperature field calculation, and the physical property parameters and the heat exchange boundary of the zigzag channel are determined mainly through an equal volume principle, and the method comprises the following steps:
step S201, determining physical parameters including a mixed heat conductivity coefficient and the like during calculation of a two-dimensional temperature field of the zigzag channel, wherein a calculation formula of the mixed heat conductivity coefficient is as follows:
，
wherein lambda is Mixing Lambda is the mixed thermal conductivity Empty space Is the heat conductivity coefficient lambda of the cooling air in the zigzag channel Fixing device For the thermal conductivity, V, of the material used for the turbine outer ring 2 A kind of electronic device V for the total volume of all the zigzag passages in the circumferential direction of the turbine outer ring 2 Fixing device Is the volume of solid of the turbine outer ring 2 at the same position of the zigzag channel.
Exemplary, V A kind of electronic device =2375.88mm 2 ，V Fixing device =6539.96 mm 2 According to the pressure of the cooling air of the turbine outer ring 2, the heat conductivity coefficient of the air between 2000 and 3000kPa is selected, and the heat conductivity coefficients are shown in the following tables 1 and 2.
TABLE 1 thermal conductivity at 20℃to 400 ℃
TABLE 2 thermal conductivity at 500℃to 900 ℃
Step S202, determining a heat exchange boundary including a mixed heat exchange coefficient and the like during calculation of a two-dimensional temperature field of the zigzag channel.
Specifically, the calculation formula of the mixed heat exchange coefficient is as follows:
，
wherein h is Mixing For the mixed heat exchange coefficient, h A kind of electronic device The heat exchange coefficient of the cooling air in the zigzag channel.
Exemplary, h A kind of electronic device =472W/(m 2 ·K)，h Mixing =63W/(m 2 ·K)。
Step S203, loading the heat exchange coefficient (the mixed heat exchange coefficient and the heat exchange coefficient of the cooling air in the zigzag channel) obtained in the step S202 to the upper boundary and the lower boundary of the zigzag channel, and loading the physical property parameter obtained in the step S201 to the region 3 between the upper boundary and the lower boundary of the zigzag channel.
Step S204, according to the methods of step S201, step S202 and step S203, combined with the general two-dimensional thermal analysis calculation method, initially completes the two-dimensional temperature field calculation (b in fig. 4), and compared with the original scheme (a in fig. 4) without using the cooling unit of the present invention, the highest temperature of the turbine casing 1 is reduced by 34K on average.
The embodiment provided by the invention is mainly used for solving the problems that the heat conduction from the turbine outer ring 2 to the turbine casing 1 is large, and a heat conduction analysis method for reducing the turbine outer ring 2 is lacking. The zigzag channel is arranged in the contact area of the turbine outer ring 2 and the turbine casing 1, so that the heat conduction from the turbine outer ring 2 to the turbine casing 1 can be effectively reduced under the condition that the force transmission between the turbine outer ring 2 and the turbine casing 1 is not influenced. The proposed analysis method based on equal volume can solve the problem of lack of analysis method.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The cooling unit for reducing heat conduction of the turbine outer ring is characterized in that the cooling unit is arranged on the turbine outer ring and is positioned in a contact area between the turbine outer ring and the turbine casing, a ventilation gap is arranged between the turbine outer ring and the turbine casing, the ventilation gap is communicated with the cooling unit, and cold air flow of the cooling unit is controlled by adjusting the gap width of the ventilation gap;
the cooling unit is provided with a plurality of zigzag channels with groove structures, the zigzag channels are arranged in the circumferential direction of the turbine outer ring, each zigzag channel comprises a first channel, a second channel and a third channel which are connected with each other, the open end of each first channel is flush with one axial side edge of the turbine outer ring, and the open end of each third channel is flush with the other axial side edge of the turbine outer ring; a first channel included angle alpha is formed between the axis of the first channel and the edge of the turbine outer ring, a second channel included angle beta is formed between the axis of the first channel and the axis of the second channel, a third channel included angle theta is formed between the axis of the second channel and the axis of the third channel, and the first channel, the second channel and the third channel have the same groove width and groove depth.
2. The cooling unit of claim 1, wherein the first channel included angle α is in the range of 30 ° to 60 °.
3. The cooling unit of claim 2, wherein the first channel angle α, the second channel angle β, and the third channel angle θ are all the same.
4. The cooling unit for reducing heat conduction of an outer ring of a turbine according to claim 1, wherein the groove depth has a value in a range of 0.4-0.6mm.
5. The cooling unit for reducing heat transfer to an outer ring of a turbine according to claim 4, wherein the groove width has a value of 3 to 5 times the groove depth.
6. The cooling unit of claim 1, wherein a plurality of the zigzag channels are uniformly arranged in a circumferential direction of the turbine outer ring.
7. A method of analyzing a cooling unit for reducing heat conduction from an outer ring of a turbine using a cooling unit for reducing heat conduction from an outer ring of a turbine according to any one of claims 1 to 6, the method comprising:
obtaining physical parameters during calculation of the two-dimensional temperature field of the zigzag channel, wherein the physical parameters comprise a mixed heat conductivity coefficient;
obtaining a heat exchange boundary of the zigzag channel during calculation of the two-dimensional temperature field, wherein the heat exchange boundary comprises a mixed heat exchange coefficient;
a two-dimensional temperature field calculation model is adopted, heat exchange boundaries comprising the mixed heat exchange coefficients are respectively loaded to the upper boundary and the lower boundary of the zigzag channel, physical property parameters comprising the mixed heat conduction coefficients are loaded to the area between the upper boundary and the lower boundary of the zigzag channel, and two-dimensional temperature field calculation is carried out;
and analyzing the temperature distribution condition of the turbine casing under the action of the cooling unit according to the two-dimensional temperature field calculation result.
8. The method of claim 7, wherein the mixed thermal conductivity is calculated by:
，
wherein lambda is Mixing Lambda is the mixed thermal conductivity Empty space Is the heat conductivity coefficient lambda of the cooling air in the zigzag channel Fixing device For the thermal conductivity of the material used for the turbine outer ring, V A kind of electronic device V for the total volume of all the zigzag passages in the circumferential direction of the turbine outer ring Fixing device Is the volume of the turbine outer ring solid at the same position of the zigzag channel.
9. The method of claim 8, wherein the formula for calculating the mixed heat transfer coefficient is:
，
wherein h is Mixing For the mixed heat exchange coefficient, h A kind of electronic device The heat exchange coefficient of the cooling air in the zigzag channel.
10. The method for analyzing a cooling unit for reducing heat conduction of a turbine outer ring according to claim 9, wherein a total volume V of all of the zigzag passages in the circumferential direction of the turbine outer ring A kind of electronic device The calculation formula of (2) is as follows:
，
volume V of the turbine outer ring solid at the same position of the zigzag passage Fixing device The calculation formula of (2) is as follows:
V fixing device =2πrxL-V A kind of electronic device ，
Wherein x is the groove depth, y is the groove width, z is the first channel length, r is the radius of the contact area, and L is the turbine outer ring axial length.
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| CN117869016B (en) | 2024-05-17 |
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