A method for establishing a double-wall vane flow heat exchange calculation model of an aero-engine

Abstract

The application belongs to the technical field of double-wall blade flow heat exchange calculation of an aero-engine, and particularly relates to a double-wall blade flow heat exchange calculation model construction method of an aero-engine, comprising the following steps: based on periodicity and symmetry, unitizing the double-wall blade to obtain a plurality of one-dimensional connected unit bodies; simplifying flow states of each unit body, modalizing the flow states of each unit body to obtain a plurality of modalized unit bodies; extracting resistance elements and heat exchange elements close to real flow; and fitting the resistance elements and the heat exchange elements for each modalized unit body to obtain a double-wall blade flow heat exchange network calculation model.

Description

A method for establishing a calculation model of flow heat transfer in double-walled blades of an aero-engine Technical Field

[0001] This application belongs to the field of flow heat transfer calculation technology for double-walled blades of aero-engines, and specifically relates to a method for constructing a flow heat transfer calculation model for double-walled blades of aero-engines. Background Technology

[0002] With the increase in thrust of aero-engines, their blades are subjected to higher temperature loads and temperature gradients, making them prone to large non-uniform deformations, which seriously affect the overall performance of the aero-engine. To address this, a double-walled blade is designed, as shown in Figure 1. The double-walled blade has an air supply chamber and multiple impact chambers. Each impact chamber surrounds the outside of the air supply chamber and contains a baffle column, which is connected to the air supply chamber through an impact hole. The outer wall of the blade has film cooling holes corresponding to the connections between the impact chambers. After the cooling air enters the air supply chamber, it enters the corresponding impact chamber through the impact holes. After being turbulent by the baffle column, it is discharged from the corresponding film cooling holes, forming a film cooling on the outer wall of the blade. This effectively cools the blade, prevents large non-uniform deformations, and ensures the overall performance of the aero-engine.

[0003] The design and iteration of double-walled blades for aero-engines require accurate acquisition of their flow and heat transfer characteristics. Currently, these characteristics are primarily obtained through the following two methods:

[0004] 1) Numerical simulation calculation method: The flow and heat transfer characteristics of double-walled blades are calculated by constructing a model of double-walled blades. However, in cases where the double-walled blade structure is complex and there are a large number of small-sized structures, a large number of meshes need to be generated, the calculation time is long, and the calculation convergence is difficult.

[0005] 2) Experimental measurement method: The flow heat transfer characteristics of double-walled blades are measured by experiment. This method has a long cycle and requires a lot of manpower and resources.

[0006] This application is made in view of the aforementioned technical deficiencies.

[0007] 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

[0008] The purpose of this application is to provide a method for constructing a computational model of flow heat transfer in aero-engine double-walled blades, so as to overcome or mitigate at least one of the known technical defects.

[0009] The technical solution of this application is:

[0010] A method for constructing a computational model for flow heat transfer in aero-engine double-walled blades includes:

[0011] Based on periodicity and symmetry, the double-walled blades are modularized to obtain multiple one-dimensional connected unit bodies;

[0012] The flow states of each unit are simplified and modalized to obtain multiple modal unit cells;

[0013] Extract resistance elements and heat exchange elements that closely resemble real flow;

[0014] For each modal unit, resistance elements and heat transfer elements are fitted to obtain a calculation model of the double-walled blade flow heat transfer network.

[0015] According to at least one embodiment of this application, in the above-described method for constructing a flow heat transfer calculation model for aero-engine double-walled blades, the extraction of resistance elements and heat transfer elements that approximate the actual flow specifically involves:

[0016] 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.

[0017] According to at least one embodiment of this application, in the above-described method for constructing a flow heat transfer calculation model for aero-engine double-walled blades, the extracted drag elements and heat transfer elements include:

[0018] The T02 element is a smooth circular tube with no rotation or heat exchange, and only flow loss is considered.

[0019] The T13 element has heat exchange losses due to the array of circular jets impacting the flat wall.

[0020] 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.

[0021] T01 element, throttling orifice without considering flow loss and heat transfer;

[0022] The T08 element features a rectangular channel with the combined effects of transverse ribs and spoiler columns.

[0023] According to at least one embodiment of this application, the above-described method for constructing a flow heat transfer calculation model for aero-engine double-walled blades further includes:

[0024] The computational model of the flow heat transfer network of the double-walled blade is optimized based on network independence analysis. The flow heat transfer topology is integrated and optimized by integrating the resistance element and the heat transfer element.

[0025] This application has at least the following beneficial technical effects:

[0026] A method for constructing a flow heat transfer calculation model for double-walled blades of aero-engines is provided. The method involves modularizing the double-walled blade into multiple one-dimensional connected units, simplifying the flow state of each unit, and modulating the flow state of each unit to obtain multiple modal units. Each modal unit is then fitted with drag and heat transfer elements to obtain a flow heat transfer network calculation model for the double-walled blade. This model is a simplified one-dimensional network model for flow heat transfer calculation of double-walled blades of aero-engines, eliminating the need for extensive mesh generation. It allows for iterative calculation of flow heat transfer without iteration, ensuring high efficiency while maintaining computational accuracy, and saving significant manpower and resources. Attached Figure Description

[0027] Figure 1 is a schematic diagram of a double-walled blade for an aero-engine;

[0028] Figure 2 is a schematic diagram of the method for constructing a flow heat transfer calculation model for aero-engine double-walled blades provided in an embodiment of this application;

[0029] Figure 3 is a schematic diagram of the modalized 141 unit body provided in an embodiment of this application;

[0030] Figure 4 is a schematic diagram of the modulated blade leading edge unit provided in an embodiment of this application;

[0031] Figure 5 is a schematic diagram of the modulated blade trailing edge blade basin side unit provided in an embodiment of this application;

[0032] Figure 6 is a schematic diagram of the modulated blade trailing edge back side unit provided in an embodiment of this application;

[0033] Figure 7 is a schematic diagram of the modal 141 unit body provided in the embodiment of this application being fitted with resistance elements and heat exchange elements.

[0034] Figure 8 is a schematic diagram of the integration of resistance elements and heat exchange elements in the modal 141 unit provided in the embodiment of this application.

[0035] 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

[0036] 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.

[0037] 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.

[0038] 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.

[0039] The present application will now be described in further detail with reference to Figures 1 to 8.

[0040] A method for constructing a computational model for flow heat transfer in aero-engine double-walled blades includes:

[0041] Step 1: Based on periodicity and symmetry, the double-walled blade is modularized to obtain multiple one-dimensional connected units, including the air supply chamber unit, the impact chamber unit, the leading edge unit, the trailing edge unit on the blade base, and the trailing edge unit on the blade back.

[0042] Step 2: Simplify the flow state of each unit body by modalizing the flow state of each unit body to obtain multiple modal unit bodies;

[0043] The air supply chamber unit corresponds to the flow of cooling air in the air supply chamber. The flow state is simplified to obtain the modal air supply chamber unit.

[0044] The impact chamber unit corresponds to the flow of cooling gas in the impact chamber. It may include multiple 141 units, corresponding to 1 impact hole, 4 turbulence columns and 1 gas film. The flow state is simplified to obtain the modal 141 unit, as shown in Figure 3.

[0045] The blade leading edge unit corresponds to the flow of cooling gas at the blade leading edge. The flow state is simplified to obtain the modal blade leading edge unit, as shown in Figure 4.

[0046] The blade trailing edge blade-side unit corresponds to the flow of cooling gas at the blade trailing edge blade-side. The flow state is simplified to obtain the modal blade trailing edge blade-side unit, as shown in Figure 5.

[0047] The blade trailing edge back side unit corresponds to the flow of cooling gas on the blade trailing edge back side. The flow state is simplified to obtain the modal blade trailing edge back side unit, as shown in Figure 6.

[0048] Step 3: Extract resistance elements and heat exchange elements that closely approximate actual flow, specifically:

[0049] Based on the aero-engine air system calculation program, and compared with the air system calculation module database, drag elements and heat exchange elements that closely resemble actual flow are selected. The extracted drag elements and heat exchange elements include:

[0050] The T02 element is a smooth circular tube with no rotation or heat exchange, and only flow loss is considered.

[0051] The T13 element has heat exchange losses due to the array of circular jets impacting the flat wall.

[0052] 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.

[0053] T01 element, throttling orifice without considering flow loss and heat transfer;

[0054] The T08 element features a rectangular channel with the combined effects of transverse ribs and spoiler columns.

[0055] Step 4: Fit each modal unit with drag elements and heat transfer elements to obtain the calculation model of the double-walled blade flow heat transfer network, where:

[0056] The modal air supply chamber unit can be fitted as a T02 element;

[0057] In the modulated 141 unit cell, the branched flow of the turbulence column 41 to 64 can be fitted to the 16T02 element, the heat exchange of the impingement hole can be fitted to the T13 element, and the gas film outlet can be fitted to the T01 element, as shown in Figure 7.

[0058] The modal blade leading edge unit, modal blade trailing edge leaf basin side unit, and modal blade trailing edge leaf back side unit can be fitted as described above, and will not be further explained here.

[0059] Step 5: Based on network independence analysis, optimize the network topology of the double-walled blade flow heat transfer network calculation model, integrate and optimize the flow heat transfer topology, and integrate the resistance elements and heat transfer elements. For example, for a modal 141 unit, the 16 T02 unit turbulent flow heat transfer regions can be used with a T08 element topology, as shown in Figure 8. Only the rib channel related parameters need to be ignored, and the column parameters are retained. The difference in flow calculation is only 0.24%, but the calculation can be greatly simplified.

[0060] The model constructed using the aforementioned method for calculating the flow and heat transfer of double-walled blades in aero-engines yields results similar to those obtained through numerical simulation. This meets the design and iteration requirements for double-walled blade designs in aero-engines. Furthermore, when applying this method, numerical simulation can be used to study the flow and heat transfer characteristics of the double-walled blades, assisting in the unitization of the blades and determining the selection of turbulence models and mesh adaptability. This ensures the accuracy of the calculated flow and heat transfer model for double-walled blades in aero-engines, resulting in accurate calculations.

[0061] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0062] 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 scope of protection 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 scope of protection of this application.

Claims

1. A method for constructing a computational model for flow heat transfer in aero-engine double-walled blades, characterized in that, include: Based on periodicity and symmetry, the double-walled blades are modularized to obtain multiple one-dimensional connected unit bodies; The flow states of each unit are simplified and modalized to obtain multiple modal unit cells; Extract resistance elements and heat exchange elements that closely resemble real flow; For each modal unit, resistance elements and heat transfer elements are fitted to obtain a calculation model of the double-walled blade flow heat transfer network.

2. The method for constructing a flow heat transfer calculation model for aero-engine double-walled blades according to claim 1, characterized in that, The extraction of resistance and heat exchange elements that closely approximate real flow involves: based on the aero-engine air system calculation program, comparing with the air system calculation module database, and selecting resistance and heat exchange elements that closely approximate real flow.

3. The method for constructing a flow heat transfer calculation model for aero-engine double-walled blades according to claim 1, characterized in that, The extracted resistance and heat exchange elements include: T02 element, a smooth circular tube with no rotation and heat exchange, considering only flow loss; T13 element, an array of circular jets with heat exchange impacting a flat wall, resulting in loss; T10 element, with heat exchange but no rotation, multiple rows of staggered circular jets impacting a semi-concave surface, resulting in loss; T01 element, a throttling orifice without considering flow loss and heat exchange; and T08 element, a rectangular channel with the combined effects of transverse ribs and turbulence columns.

4. The method for constructing a flow heat transfer calculation model for aero-engine double-walled blades according to claim 1, characterized in that, It also includes: seeking network topology optimization for the double-walled blade flow heat transfer network calculation model based on network independence analysis, integrating and optimizing the flow heat transfer topology, and integrating resistance elements and heat transfer elements.

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