A method for designing a turbine micro-rib double-wall vane of an aero-engine
By using CFX numerical calculations and one-dimensional flow heat transfer network analysis, the problem of measuring and calculating the temperature distribution and cooling gas consumption of turbine micro-ribbed double-walled guide vanes was solved. This enabled precise control of the cooling gas consumption and uniformity of the temperature distribution, thereby improving the cooling efficiency and structural strength of the turbine micro-ribbed double-walled guide vanes.
Patent Information
- Application Number
- CN202211739312.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2022-12-31
- Publication Date
- 2026-02-10
- Estimated Expiration
- 2042-12-31
AI Technical Summary
Existing technologies make it difficult to accurately measure and calculate the temperature distribution and cooling gas consumption of turbine microribbed double-walled guide vanes, resulting in large design errors, long calculation times, and difficulty in meeting the cooling requirements of aero engines in high-temperature environments.
The CFX numerical calculation method and SST k-ω turbulence model were used to analyze the airflow characteristics of the cooling air inside the guide vane. A one-dimensional flow heat transfer calculation network was constructed. Combined with the aero-engine air system calculation program, the resistance and heat transfer elements that approximate the actual flow were extracted. Internal flow heat transfer calculation and three-dimensional temperature field analysis were performed, and the guide vane structural parameters were adjusted to achieve the design specifications.
It achieves precise control of the cooling air consumption of the guide vanes and uniform temperature distribution, reduces the thermal stress of the guide vanes, improves the cooling efficiency and structural strength of the turbine micro-ribbed double-walled guide vanes, and meets the requirements for use in high-temperature environments.
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Figure CN116108562B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the technical field of microribbed double-walled guide vane design for aero-engine turbines, specifically relating to a design method for microribbed double-walled guide vanes for aero-engine turbines. Background Technology
[0002] It is generally believed that, assuming the size of the aircraft engine remains unchanged, the engine thrust can increase by approximately 10% for every 100°C increase in turbine inlet temperature.
[0003] With the iteration of technology, the turbine inlet temperature in aero engines is constantly increasing. The turbine guide vanes directly bear the extremely high initial gas temperature of the non-uniform flame at the combustion chamber outlet. Therefore, high temperature resistance is an important indicator of turbine guide vanes.
[0004] Employing a micro-ribbed double-walled structure, the turbine guide vanes of aero-engines can be cooled efficiently with a relatively small amount of cooling air. Micro-ribbed double-walled guide vanes, such as... Figure 1 As shown, its blade has multiple air supply chambers and lamellae chambers, and multiple film pores on the sidewalls. Each air supply chamber has an inlet at the root or head of the blade. Each lamellae chamber is connected by multiple impact holes arranged along the blade height. The lamellae chambers are supported by multiple microribs arranged along the blade height. Each film pore communicates with its corresponding lamellae chamber. Figure 2 As shown.
[0005] When the aero-engine is working, cooling air is introduced into each air supply chamber of the turbine microrib double-walled guide vane. The cooling air enters the corresponding layer plate cavity through each impact hole for impact cooling. After being turbulent by the microrib, it flows out through the film cooling hole and forms a film on the side wall of the blade, achieving efficient cooling of the guide vane.
[0006] When designing turbine micro-ribbed double-walled guide vanes, it is necessary to obtain the temperature changes at different positions in the chord and radial directions of the guide vane, the cold air flow rate, and the pressure and temperature distribution in the main combustion zone. The goal is to balance the cold air flow rate, flatten the temperature gradient, reduce the thermal stress of the guide vane, and obtain an air-cooled guide vane with a relatively uniform temperature distribution and a small required amount of cold air within the allowable temperature of the guide vane material.
[0007] Currently, when designing turbine microribbed double-walled guide vanes, experimental measurement methods and numerical calculation methods are mostly used to obtain the temperature distribution on the guide vanes, among which:
[0008] 1) For experimental measurement methods, due to the large number of impact holes, microribs, and film vents inside the turbine microrib double-walled guide vane, the structure is extremely complex. The flow at each position is asymmetrical, and the heat transfer coefficients of each surface are unevenly distributed. It is difficult to measure the wall temperature distribution of each part of the guide vane under the working state of the aero-engine through experimental methods, and the measurement results have a very large error.
[0009] 2) Numerical calculation methods often directly employ fluid-structure interaction (FSI) to calculate the temperature distribution of turbine micro-ribbed double-walled guide vanes. FSI methods are mainly divided into alternating solution methods and global solution methods. The alternating solution method is based on dividing the solution domain into a fluid domain and a solid domain according to the different media. During the solution process, the governing equations of the fluid domain and the solid domain are iterated alternately in time and space. The coupled iteration process is asynchronous, hence the name alternating solution method. It is mainly suitable for solving FSI problems of steady or incompressible fluids. The global solution method places the governing equations of the fluid domain and the solid domain in the same closed system of equations and discretizes them simultaneously, solving them within a time step. It is mainly suitable for solving highly transient FSI problems of compressible fluids. FSI methods require solving large nonlinear algebraic equation systems, which places very high demands on computer hardware and consumes a lot of computation time, making it difficult to apply in engineering calculations.
[0010] This application is made in view of the aforementioned technical deficiencies.
[0011] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention
[0012] The purpose of this application is to provide a design method for microribbed double-walled guide vanes for aero-engine turbines, in order to overcome or mitigate at least one of the known technical defects.
[0013] The technical solution of this application is:
[0014] A design method for a microribbed, double-walled guide vane for an aero-engine turbine includes:
[0015] Analyze the airflow characteristics of the cooling air inside the guide vane;
[0016] Extract resistance elements and heat exchange elements that closely resemble real flow;
[0017] A one-dimensional flow heat transfer calculation network is obtained by fitting the air supply cavity, impact hole, laminate cavity, micro rib, and air film hole on the guide vane with resistance element and heat transfer element in series.
[0018] Based on a one-dimensional flow heat transfer calculation network, considering the temperature rise of the cooling gas along the flow path, internal flow heat transfer calculation is performed to obtain the cooling gas consumption and heat transfer parameters of the guide vane. The guide vane structural parameters are then adjusted to ensure that the cooling gas consumption of the guide vane reaches the design target.
[0019] A three-dimensional temperature field calculation model of the guide vane is constructed, heat transfer parameters are set, the temperature distribution on the guide vane is calculated, and the structural parameters of the guide vane are adjusted so that the temperature distribution of the guide vane reaches the design target.
[0020] Perform guide vane strength calculations and adjust guide vane structural parameters to ensure that the guide vane strength meets design specifications.
[0021] According to at least one embodiment of this application, in the above-mentioned design method of micro-ribbed double-walled guide vanes for aero-engine turbines, the flow characteristics of cooling airflow at typical local locations within the guide vane are analyzed, specifically by using the CFX numerical calculation method and the SST k-ω turbulence model for calculation and analysis.
[0022] According to at least one embodiment of this application, in the above-described design method for micro-ribbed double-walled guide vanes of aero-engine turbines, drag elements and heat exchange elements that closely approximate real flow are extracted, specifically as follows:
[0023] Based on the aero-engine air system calculation program, and compared with the air system calculation module database, resistance elements and heat exchange elements that closely approximate real flow are selected.
[0024] According to at least one embodiment of this application, in the above-described design method for microribbed double-walled guide vanes of aero-engine turbines, the extracted drag elements and heat exchange elements include:
[0025] T02 element, a smooth circular tube with no rotation and heat exchange, considering only flow loss;
[0026] The T10 element has heat exchange but no loss due to the impact of multiple rows of staggered circular jets on the semi-concave surface.
[0027] The T13 element has heat exchange losses due to the array of circular jets impacting the flat wall.
[0028] T01 element, throttling orifice without considering flow loss and heat transfer;
[0029] The T14 element is a smooth circular tube with heat exchange, localized losses, and flow resistance.
[0030] According to at least one embodiment of this application, in the above-described design method for aero-engine turbine micro-ribbed double-walled guide vanes, the guide vane is divided into multiple segments along the blade height direction. The characteristic surface parameters are used to represent the average of each segment when calculating the gas pressure boundary parameters of each segment. Virtual units are introduced to balance radial pressure and temperature. Based on a one-dimensional flow heat transfer calculation network, the internal flow heat transfer calculation is performed considering the temperature rise of the cooling gas along the blade to obtain the cooling gas consumption and heat transfer parameters of the guide vane. The guide vane structural parameters are adjusted so that the cooling gas consumption of the guide vane reaches the design target. Attached Figure Description
[0031] Figure 1This is a schematic diagram of a micro-ribbed double-walled guide vane for an aero-engine turbine.
[0032] Figure 2 This is a schematic diagram of the impact hole, microrib, and film cooling hole of the double-walled guide vane of the microrib of an aero-engine turbine.
[0033] Figure 3 This is a schematic diagram of the design method for a micro-ribbed double-walled guide vane of an aero-engine turbine provided in the embodiments of this application;
[0034] Figure 4 This is a schematic diagram of the flow characteristics of a structure with five periodically arranged units within an independent laminate cavity provided in an embodiment of this application;
[0035] Figure 5 This is a schematic diagram of a one-dimensional flow heat transfer calculation network for a micro-ribbed double-walled guide vane unit structure of an aero-engine turbine provided in an embodiment of this application;
[0036] Figure 6 This is a schematic diagram provided in an embodiment of the present application, showing a micro-ribbed double-walled guide vane for an aero-engine turbine divided into five segments along its radial height;
[0037] Figure 7 This is a schematic diagram of a one-dimensional flow heat transfer calculation network for an air supply chamber and a connecting blade basin side and blade back side layer plate cavity in a micro-ribbed double-walled guide vane of an aero-engine turbine provided in an embodiment of this application.
[0038] Figure 8 This is a schematic diagram of the design of the cooling gas consumption and heat transfer coefficient of each exhaust film hole of the micro-ribbed double-walled guide vane of the aero-engine turbine provided in the embodiments of this application;
[0039] Figure 9 This is a schematic diagram of the heat exchange partition of the micro-ribbed double-walled guide vane of an aero-engine turbine provided in an embodiment of this application;
[0040] Figure 10 This is a schematic diagram of the heat transfer analysis of the micro-ribbed double-walled guide vane of the aero-engine turbine provided in the embodiments of this application.
[0041] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation
[0042] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.
[0043] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.
[0044] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.
[0045] The following is in conjunction with the appendix Figures 1 to 5 This application will be described in further detail.
[0046] This application provides a design method for a micro-ribbed, double-walled guide vane for an aero-engine turbine, such as... Figure 3 As shown, the specific process can be found below.
[0047] 1. Analyze the airflow characteristics of the cooling air inside the guide vane.
[0048] The flow characteristics of typical unit structures at guide vane locations were calculated and analyzed using the CFX numerical method and the SST k-ω turbulence model. One unit structure was assigned to one impact hole. Figure 4 The flow characteristics of a structure consisting of five periodically arranged unit cells within an independent laminate cavity.
[0049] a) Overall flow characteristics of the micro-ribbed double-walled guide vane unit structure
[0050] Within a single unit structure, cooling gas flows out from the impact hole and impacts the guide vane wall. The vortex that follows the impact on the guide vane wall in the opposite direction of the swirling transverse channel occupies the square cross-section channel formed by the micro-ribs.
[0051] b) Lateral channel flow characteristics of micro-ribbed double-walled guide vane unit structure with periodic distribution
[0052] The flow within the transverse channel is not only the swirling channel vortex after impacting the guide vane wall, but also the rebound flow after touching the transverse micro-ribs. The two vertical vortex systems entrain and mix with each other, improving the heat transfer characteristics within the transverse channel.
[0053] c) Periodic distribution and radial channel flow characteristics of the micro-ribbed double-walled guide vane unit structure
[0054] After passing through the complex flow in the transverse channel, the cooling air meets in the radial channel. At this point, only part of the momentum of the vortex flow is consumed, and there will still be turbulent vortex mixing, but the vortex intensity is far less than that in the transverse channel.
[0055] 2. Extract resistance elements and heat exchange elements that closely resemble real flow.
[0056] Based on the aero-engine air system calculation program, and comparing it with the air system calculation module database, drag elements and heat exchange elements that closely approximate actual flow are selected as follows:
[0057] T02 element, a smooth circular tube with no rotation and heat exchange, considering only flow loss;
[0058] The T10 element has heat exchange but no loss due to the impact of multiple rows of staggered circular jets on the semi-concave surface.
[0059] The T13 element has heat exchange losses due to the array of circular jets impacting the flat wall.
[0060] T01 element, throttling orifice without considering flow loss and heat transfer;
[0061] The T14 element is a smooth circular tube with heat exchange, localized losses, and flow resistance.
[0062] 3. Construct a one-dimensional flow heat transfer computational network for the guide vanes.
[0063] Based on the airflow characteristics of the cooling air inside the guide vane, the air supply chamber is modeled as a smooth circular tube element T02, the outflow from the chord and trailing edge impact holes is modeled as a flat plate impact heat exchange element T13, the outflow from the leading edge impact holes is modeled as an impact semi-concave surface heat exchange element T10, the air film holes are modeled as a throttling orifice element T01, and the micro-ribbed channels are modeled as heat exchange circular tube elements T14, thus constructing a one-dimensional flow heat transfer calculation network for the guide vane.
[0064] The one-dimensional flow heat transfer computational network of the micro-ribbed double-walled guide vane unit structure of aero-engine turbine is as follows: Figure 5 As shown, the flow in the transverse channel of the microrib is simplified to pipe flow. However, the turbulent kinetic energy intensity of the vortex system in this transverse channel is much stronger than that of simple pipe flow, so it can only be used as an approximate model. The heat transfer coefficient value of the pipe flow is lower than the actual value. The impinging jet is constrained by the microrib in the chord direction, and the model of the impinging heat transfer radial flow is higher than the actual value. The compromise between the two is close to the actual heat transfer. The flow in the radial channel of the microrib is also modeled as pipe flow. The heat transfer characteristics in the radial channel are closer to the heat transfer characteristics of pipe flow.
[0065] Aero-engines have high peak gas temperatures and large radial temperature gradients. Based on the second part of the modeling principle, the micro-ribbed double-walled guide vane is decomposed for analysis closer to the actual solution. The guide vane is divided into five segments along its radial height. The gas pressure boundary parameters for each segment are calculated using characteristic surface parameters to represent the average values of each segment. Figure 6 As shown.
[0066] Virtual units are introduced into the one-dimensional flow heat transfer calculation network to balance radial pressure and temperature, avoid airflow pressure loss that does not match the actual situation caused by multi-cavity confluence, and fit the flow process inside the guide vane as impingement heat transfer - pipe flow heat transfer - air film outflow.
[0067] In the microribbed double-walled guide vane of an aero-engine turbine, the No. 3 air supply chamber is connected to the No. 10 layer plate cavity located at the blade head and the No. 2 layer plate cavity on the blade back via impact holes. See details... Figure 1 To address this, a one-dimensional flow heat transfer computational network is constructed, such as... Figure 7 As shown.
[0068] 4. Analysis of Cooling Air Consumption
[0069] Based on the aero-engine air system calculation program AIRSYS4, and according to the cooling structure of the turbine micro-ribbed double-walled guide vane, the one-dimensional flow heat transfer calculation network, and the cooling unit decomposition method, the flow heat transfer calculation criteria of the corresponding modular elements are adopted, and the geometric data of the unit model are extracted. The internal flow heat transfer calculation of the micro-ribbed double-walled guide vane considering the temperature rise of the cold air along the blade is carried out. The cold air volume and heat transfer parameters of each unit structure of the guide vane are obtained. By adjusting the structural parameters of the cooling unit, the rapid iteration of the cooling air volume is achieved, so that the cooling air volume of the guide vane reaches the design target.
[0070] The optimized design of the turbine micro-ribbed double-walled guide vane ensures that the cooling air volume of each exhaust film hole is strictly designed according to the heat transfer coefficient distribution law of the guide vane, achieving body-fit cooling and ensuring high cooling temperature drop with less cooling air volume. Figure 8 As shown.
[0071] 5. Temperature Distribution Analysis
[0072] A three-dimensional temperature field calculation model for a turbine micro-ribbed double-walled guide vane was established based on the ANSYS computing platform. (Refer to...) Figure 6 Perform heat exchange zoning, specifically as follows: Figure 9 As shown, thermal analysis is performed, with the heat transfer coefficient and heat transfer temperature on the gas wall grid nodes interpolated as the external heat transfer of the guide vane. The internal cooling heat transfer boundary conditions are extracted from the one-dimensional internal flow heat transfer calculation results. The third type of boundary conditions are set to solve the three-dimensional temperature field of the guide vane. By adjusting the structural parameters of the cooling unit, the three-dimensional temperature field is rapidly iterated so that the three-dimensional temperature field of the guide vane can meet the usage requirements of the guide vane material.
[0073] The micro-ribbed transverse flow channel is considered as a T14 heat exchanger tube flow. The heat transfer coefficient is the same on all sides of the channel. A weighted average of the impingement heat transfer and transverse tube flow heat transfer at that location is used to compromise between the impingement jet and transverse flow element modeling. The micro-ribbed radial channel is also equivalent to a T14 tube flow. Figure 10 As shown, the temperature field of the guide vane is iterated. By adjusting the structural parameters of the cooling unit, the temperature difference of the guide vane cross section is reduced, thereby reducing the thermal stress and alternating stress of the guide vane.
[0074] 6. Strength Analysis
[0075] The strength of the guide vanes is calculated, and the strength is rapidly iterated by adjusting the structural parameters of the cooling unit, so that the strength of the guide vanes can meet the usage requirements of the guide vane environment.
[0076] The core and primary technical aspect of the aforementioned design method for microribbed double-walled guide vanes for aero-engine turbines is the establishment of a highly accurate calculation method for flow and heat transfer in double-walled structures.
[0077] Based on the flow characteristics analysis of micro-ribbed double-walled guide vanes of aero-engine turbines, a one-dimensional flow heat transfer calculation network is established to simplify the complex three-dimensional heat transfer problem into a one-dimensional flow heat transfer calculation.
[0078] Considering the temperature rise of the cooling gas along the flow path, a one-dimensional network method is applied to reasonably decompose the complex high-density micro-flow unit into a unit that closely approximates the actual internal flow and heat transfer. The established one-dimensional flow heat transfer network rapid calculation method can quickly analyze the influence of micro-ribbed double-wall structural elements and airflow parameters on its flow heat transfer characteristics.
[0079] The aforementioned design method for microribbed double-walled guide vanes for aero-engine turbines can achieve rapid iterative design of heat transfer inside the guide vane, quickly realize the adjustment and optimization design of local cooling structures of the guide vane, and is widely used in engineering design calculations for cooling structures of microribbed double-walled guide vanes.
[0080] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of this application.
Claims
1. A design method for a microribbed double-walled guide vane for an aero-engine turbine, characterized in that, include: Analyze the airflow characteristics of the cooling air inside the guide vane; Extract resistance elements and heat exchange elements that closely resemble real flow; A one-dimensional flow heat transfer calculation network is obtained by fitting the air supply cavity, impact hole, laminate cavity, micro rib, and air film hole on the guide vane with resistance element and heat transfer element in series. Based on a one-dimensional flow heat transfer calculation network, considering the temperature rise of the cooling gas along the flow path, internal flow heat transfer calculation is performed to obtain the cooling gas consumption and heat transfer parameters of the guide vane. The guide vane structural parameters are then adjusted to ensure that the cooling gas consumption of the guide vane reaches the design target. A three-dimensional temperature field calculation model of the guide vane is constructed, heat transfer parameters are set, the temperature distribution on the guide vane is calculated, and the structural parameters of the guide vane are adjusted so that the temperature distribution of the guide vane reaches the design target. Perform guide vane strength calculations and adjust guide vane structural parameters to ensure that the guide vane strength meets design specifications. Extracting resistance elements and heat exchange elements that closely resemble real flow, specifically: Based on the aero-engine air system calculation program, and compared with the air system calculation module database, resistance elements and heat exchange elements that closely resemble real flow are selected; The extracted resistance elements and heat exchange elements include: T02 element, a smooth circular tube with no rotation and heat exchange, considering only flow loss; The T10 element features heat exchange and non-rotating multi-row staggered circular jets impacting a semi-concave surface. The T13 element features an array of circular jets that impact a flat wall for heat exchange. T01 element, throttling orifice without considering flow loss and heat transfer; The T14 element is a smooth circular tube with heat exchange, localized losses, and flow resistance.
2. The design method for microribbed double-walled guide vanes of aero-engine turbines according to claim 1, characterized in that, The flow characteristics of the cooling airflow inside the guide vane were analyzed, specifically by using the CFX numerical calculation method and the SST k-ω turbulence model.
3. The design method for microribbed double-walled guide vanes of aero-engine turbines according to claim 1, characterized in that, Based on a one-dimensional flow heat transfer calculation network, considering the temperature rise of the cooling gas along the flow path, internal flow heat transfer calculation is performed to obtain the cooling gas consumption and heat transfer parameters of the guide vane. The guide vane structural parameters are adjusted so that the cooling gas consumption of the guide vane reaches the design target. The guide vane is divided into multiple segments along the blade height direction. The characteristic surface parameters are used to represent the average of each segment for calculating the gas pressure boundary parameters. Virtual elements are also introduced to balance the radial pressure and temperature.