Engine rotor blade tip multi-parameter design method and system, and related device

Abstract

The application provides an engine rotor blade tip multi-parameter design method, system and related device, relates to the rotor blade tip design technical field, and the design method comprises the following steps: S1, calculating a blade tip deformation amount, and drawing a blade tip thermal profile; S2, according to the blade tip thermal profile and the blade tip deformation amount, a blade tip final shape is drawn; S3, the deformation amount of a machine case is calculated, and a machine case cold profile is drawn; and S4, according to the machine case cold profile and the blade tip final shape, the cold installation gap of the blade tip and the machine case is determined. The application can ensure the safe operation of the engine under the condition of ensuring the performance requirements of the engine, and greatly improves the rationality of the gap design.

Description

Technical Field

[0001] This invention relates to the field of aero-engine rotor blade tip design technology, specifically to a multi-parameter design method, system, and related device for engine rotor blade tips. Background Technology

[0002] The design of rotor blade tip clearance in aero-engines has a significant impact on engine safety and performance. If the blade tip clearance is too small, there is a risk of abrasion of the coating and even the metal substrate of the casing, affecting safe engine operation. If the blade tip clearance is too large, engine performance will be affected. The blade tip clearance mainly consists of two parts: the rotor blade tip and the casing flow channel. The casing flow channel is generated by aerodynamic design and is determined early in the design process, generally remaining unchanged in subsequent designs. Therefore, the final blade tip clearance is mainly determined by the rotor blade tip shape. Traditionally, the blade tip shape is designed linearly, roughly parallel to the casing, based on the casing shape. The clearance is given empirically and adjusted later through testing. However, with technological advancements, aerodynamic shapes have become more complex, and the deformation of the blades and casing has also become more intricate. This traditional design method, primarily based on experience, is increasingly unable to meet design requirements, mainly due to the following problems:

[0003] 1) There are no fixed methods or guidelines for the design of gaps and blade tip shapes. Human factors play a significant role, and the design results vary greatly among different designers, resulting in poor repeatability and traceability.

[0004] 2) The gap and blade tip shape are generally determined through multiple experiments, which is time-consuming and costly;

[0005] 3) The blade design is becoming increasingly complex, often using composite swept blades. The deformation of the blade tip varies greatly from front to back. Traditional empirical methods do not take into account the influence of blade and casing deformation. Even if the final size and clearance are determined through multiple experiments, the limited experimental monitoring data still makes it impossible to effectively control the blade tip clearance during operation. Generally, areas with large deformation are prone to scratching the casing, while areas with small deformation have large clearances that are unknown.

[0006] In view of this, the inventors of this application have designed a multi-parameter design method, system and related device for engine rotor blade tips in order to overcome the above-mentioned technical problems. Summary of the Invention

[0007] The technical problem to be solved by the present invention is to overcome the shortcomings of the traditional engine rotor design method in the prior art, which is difficult to meet the requirements of blade tip clearance and blade tip shape, and to provide a multi-parameter design method, system and related device for engine rotor blade tips.

[0008] The present invention solves the above-mentioned technical problems through the following technical solution:

[0009] This invention provides a multi-parameter design method for engine rotor blade tips, characterized in that the design method includes the following steps: S1, calculating the blade tip deformation and drawing the hot profile of the blade tip; S2, drawing the final shape of the blade tip based on the hot profile and the blade tip deformation; S3, calculating the casing deformation and drawing the casing cold profile; S4, determining the cold installation gap between the blade tip and the casing based on the casing cold profile and the final shape of the blade tip.

[0010] According to one or more embodiments of the present invention, step S1 includes the following steps: S 11 Perform combined calculations on the rotor and stator blades, and calculate the rotor blade tip deformation; S 12 1. Determine several axial positions of the rotor blade tip and extract the blade tip deformation; S 13 Set the hot design gap between the blade tip and the casing, and draw the hot profile of the blade tip based on the casing profile in operation.

[0011] According to one or more embodiments of the present invention, step S 11 In the calculation, the rotor blade tip deformation is calculated using the finite element method. The rim deformation is determined by two-dimensional calculation, and the change of the blade tip relative to the rim is determined by three-dimensional calculation. The rotor blade tip deformation is obtained by superimposing the rim deformation and the change of the blade tip relative to the rim.

[0012] According to one or more embodiments of the present invention, step S 12 Includes the following steps: S 121 Based on the uniform selection of blade width along the axial direction, determine several axial positions P1, P2…Pn of the rotor blade tip; S 122 Extract the multi-point axial deformation of the blade tip δ1, δ2...δn; the blade tip deformation is the multi-point axial deformation of the blade tip δ1, δ2...δn.

[0013] According to one or more embodiments of the present invention, step S2 includes the following steps: S 21 Based on the hot profile and deformation of the blade tip, draw the cold profile of the blade tip; 22 Based on the cold profile of the leaf tip, perform multi-segment linear fitting of the leaf tip to draw the final shape of the leaf tip.

[0014] According to one or more embodiments of the present invention, step S3 includes the following steps: S 31 1. Perform stator casing deformation calculations to determine several axial positions of the casing and extract the deformation amount; S 32 Based on the casing profile in its operating state, and according to the deformation of the casing, the casing profile in its cold state is drawn.

[0015] According to one or more embodiments of the present invention, step S31 Includes the following steps: S 311 1. Select uniformly along the axial direction of the casing to determine several axial positions N1, N2…Nn of the casing; S 312 Extract the axial multi-point deformation amounts Δ1, Δ2...Δn of the casing; the deformation amount of the casing is obtained by using the axial multi-point deformation amounts Δ1, Δ2...Δn of the casing.

[0016] This invention also provides a multi-parameter design system for engine rotor blade tips, characterized in that the design system adopts the multi-parameter design method for engine rotor blade tips as described above. The design system includes: a blade tip simulation module for calculating blade tip deformation, drawing the hot profile of the blade tip, and drawing the final shape of the blade tip based on the hot profile and the blade tip deformation; a casing simulation module for calculating casing deformation and drawing the cold profile of the casing; and a calculation module for determining the cold installation clearance between the blade tip and the casing based on the cold profile of the casing and the final shape of the blade tip.

[0017] The present invention also provides an electronic device, characterized in that it includes a processor and a memory, the memory storing a program or instructions, the processor executing the program or instructions, causing the electronic device to perform the engine rotor blade tip multi-parameter design method as described above.

[0018] The present invention also provides a readable storage medium, characterized in that the readable storage medium stores a program or instructions, and when the program or instructions are run on an electronic device, the electronic device executes the engine rotor blade tip multi-parameter design method as described above.

[0019] The positive and progressive effects of this invention are as follows:

[0020] The multi-parameter design method, system, and related devices for engine rotor blade tips of the present invention have at least the following advantages:

[0021] This invention presents a multi-parameter design method for engine rotor blade tips, which is a multi-parameter, multi-objective blade tip design method that significantly improves the rationality of clearance design compared to traditional experience-based design methods. The multi-parameter design method, system, and related devices of this invention introduce multi-point deformation at the rotor and stator blade tip positions when designing blade tip clearance and shape, and determine the blade tip size segmentally based on the deformation. This method effectively solves the problems of uneven blade tip deformation before and after deformation, resulting in some areas of scraping and some areas of excessive clearance, ensuring both safe engine operation and performance requirements. Furthermore, the improved design accuracy effectively reduces experimental iterations, shortens the cycle time, and reduces costs. In addition, the proposed method clarifies the process, making the design process systematic, traceable, and repeatable. Attached Figure Description

[0022] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features, wherein:

[0023] Figure 1 This is a schematic diagram of the casing and blade tip in cold and hot states in the multi-parameter design method of engine rotor blade tip of the present invention.

[0024] Figure 2 This is a schematic diagram of the blade tip segment fitting in the multi-parameter design method for engine rotor blade tips of the present invention.

[0025] Figure 3 This is a schematic diagram of the cold-state blade tip clearance in the multi-parameter design method for engine rotor blade tips of the present invention.

[0026] Figure 4 This is a schematic diagram of the conventional blade tip profile scraping process.

[0027] Figure 5 This is a schematic diagram of the thermal state of the blade tip profile designed by the multi-parameter design method for engine rotor blade tips according to the present invention. Detailed Implementation

[0028] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0029] Embodiments of the invention will now be described in detail with reference to the accompanying drawings. Preferred embodiments of the invention will now be described in detail, examples of which are illustrated in the drawings. Wherever possible, the same reference numerals will be used in all the drawings to denote the same or similar parts. Furthermore, although the terminology used herein is selected from commonly known and used terminology, some terms mentioned in this specification may have been chosen by the applicant at his or her discretion, and their detailed meanings are explained in the relevant sections of the description herein. Moreover, the invention should be understood not only by the actual terms used, but also by the meaning implied by each term.

[0030] This invention provides a multi-parameter design method for engine rotor blade tips, the design method comprising the following steps:

[0031] Step S1: Calculate the blade tip deformation and draw the desired blade tip thermal profile 200.

[0032] Step S2: Draw the final shape 400 of the blade tip based on the desired hot profile 200 of the blade tip and the amount of blade tip deformation.

[0033] Step S3: Deformation of the computer housing; draw the cold-state profile of the housing at 500.

[0034] Step S4: Determine the cold installation gap between the blade tip and the casing based on the cold profile 500 of the casing and the final shape 400 of the blade tip.

[0035] Preferably, in step S1, a composite deformation calculation of the rotor and rotor blades is performed to obtain the rotor blade tip deformation. Then, the axial deformation of the blade tip at multiple points is extracted. The rotor blade tip deformation is generally linear or parabolic along the axial direction. If it is not this shape, the blade shape can be appropriately iterated to control the blade tip deformation.

[0036] Preferably, in step S4, the cold mounting gap D between the blade tip and the casing is determined based on the cold profile 500 of the casing and the final shape 400 of the blade tip. This gap must ensure that the assembly is feasible.

[0037] The multi-parameter design method for engine rotor blade tips in this invention has a clear process to follow, strong traceability, and high design repeatability. The design incorporates the deformation of the blades and casing, and determines the blade tip shape and clearance based on the deformation results, ensuring high reliability. It effectively solves the problem of uneven blade tip clearance, avoiding situations where some blade tip areas are scraped or have large clearances in other areas. This effectively ensures that the clearance is reasonable during engine operation, meeting performance and safe operation requirements. Simultaneously, the accuracy of clearance design is improved, effectively reducing the number of test iterations, shortening the cycle time, and reducing costs.

[0038] In a preferred embodiment of the multi-parameter design method for engine rotor blade tips of the present invention, step S1 includes the following steps:

[0039] Step S 11 Perform composite calculations on the rotor and stator blades, and calculate the rotor blade tip deformation.

[0040] Step S 12 1. Determine several axial positions of the rotor blade tip and extract the blade tip deformation;

[0041] Step S 13 Set the hot design gap between the blade tip and the casing. Based on the casing profile 100 in operation, draw the desired hot profile 200 of the blade tip.

[0042] Preferably, in step S 13 In this paper, assuming that the hot design gap between the blade tip and the casing is d when the engine is running, the desired hot profile of the blade tip 200 under the operating state is drawn based on the casing profile 100 under the operating state.

[0043] As a preferred embodiment of the multi-parameter design method for engine rotor blade tips of the present invention, step S 11In the calculation, the rotor blade tip deformation is calculated using the finite element method. The rim deformation is determined by two-dimensional calculation, and the change of the blade tip relative to the rim is determined by three-dimensional calculation. The final rotor blade tip deformation is obtained by superimposing the rim deformation and the change of the blade tip relative to the rim.

[0044] It should be noted that, to improve calculation accuracy, the finite element method is typically used. The rotor disk has a periodically symmetrical structure, so two-dimensional calculations are employed to determine the rim deformation. The blade sweep, with its complex structure, is calculated in three dimensions to determine the change in blade tip deformation relative to the rim. The final blade tip deformation is obtained by superimposing the rim deformation with the blade tip deformation relative to the rim.

[0045] As a preferred embodiment of the multi-parameter design method for engine rotor blade tips of the present invention, step S 12 Includes the following steps:

[0046] Step S 121 Based on the uniform selection of blade width along the axial direction, determine several axial positions P1, P2...Pn of the rotor blade tip;

[0047] Step S 122 Extract the axial deformation of multiple points δ1, δ2…δn at the blade tip;

[0048] The blade tip deformation is defined as the multi-point deformation δ1, δ2…δn along the blade tip axis.

[0049] It should be noted that, as Figure 1 As shown, several axial positions P1, P2...Pn of the rotor blade tip are determined. These positions can be uniformly selected based on the blade width along the axial direction. Then, the axial deformation amounts δ1, δ2...δn of the blade tip are extracted. The rotor blade tip deformation is generally linear or parabolic along the axial direction. If it is not this shape, the blade shape can be iterated appropriately to control the blade tip deformation. Figure 1 The image shows the hot and cold states of the casing 600 and the blade tip 700.

[0050] In a preferred embodiment of the multi-parameter design method for engine rotor blade tips of the present invention, step S2 includes the following steps:

[0051] Step S 21 Based on the desired hot profile 200 of the blade tip and the blade tip deformation, draw the desired cold profile 300 of the blade tip.

[0052] Step S 22 Based on the desired cold profile 300 of the blade tip, perform multi-segment linear fitting of the blade tip to draw the final shape 400 of the blade tip.

[0053] Preferably, in step S 21In the process, based on the desired hot profile 200 of the blade tip and the blade tip deformation amounts δ1, δ2...δn, the desired cold profile 300 of the blade tip is drawn.

[0054] Preferably, such as Figure 2 As shown, step S 22 Based on the desired cold profile 300 of the blade tip, perform multi-segment linear fitting of the blade tip to draw the final multi-segment fitted shape of the blade tip. The final multi-segment fitted shape of the blade tip is the final shape 400 of the blade tip. The error X between the final shape 400 of the blade tip and the desired cold profile 300 of the blade tip must meet the design requirements. Figure 2 The segmented fitting of the leaf tip at 700mm is shown.

[0055] In a preferred embodiment of the multi-parameter design method for engine rotor blade tips of the present invention, step S3 includes the following steps:

[0056] Step S 31 1. Conduct deformation calculations of the stator casing, determine several axial positions of the casing, and extract the deformation amount of the casing;

[0057] Step S 32 Based on the casing outline 100 in the operating state, the casing cold state outline 500 is drawn according to the deformation of the casing.

[0058] As a preferred embodiment of the multi-parameter design method for engine rotor blade tips of the present invention, step S 31 Includes the following steps:

[0059] Step S 311 1. Select uniformly along the axial direction of the casing to determine several axial positions N1, N2...Nn of the casing;

[0060] Step S 312 Extract the axial deformation of the casing at multiple points Δ1, Δ2…Δn;

[0061] The deformation of the casing is expressed as the axial multi-point deformation Δ1, Δ2...Δn of the casing.

[0062] It should be noted that, as Figure 3 As shown, the deformation calculation of the stator casing is carried out to determine several axial positions N1, N2...Nn of the rotor blade tip casing. When determining these positions, they can be uniformly selected according to the blade width along the axial direction. Then, the axial deformation of the blade tip casing at multiple points Δ1, Δ2...Δn is extracted.

[0063] Preferably, step S 32 Based on the casing profile 100 in operation, the casing profile 500 in cold state is drawn according to the deformation amounts Δ1, Δ2...Δn of the casing.

[0064] like Figure 4As shown, the blade tip shape is determined by the casing profile using conventional design methods. When the deformation of the leading and trailing edges of the blade is greater than the deformation in the middle position, scraping of the leading and trailing edges will occur. Figure 4 The diagram shows the casing outline 100 in operation, the desired blade tip cold state outline 300, and the desired blade tip hot state outline 200.

[0065] like Figure 5 The image shows the blade tip profile of the multi-parameter design method for engine rotor blade tips according to the present invention. Based on the deformation of the leading and trailing edges, the shape of the leading and trailing edge blade tip has been modified to ensure a more uniform gap between the hot state and the casing. Figure 5 The diagram shows the casing outline 100 in operation, the desired blade tip cold state outline 300, and the desired blade tip hot state outline 200.

[0066] The present invention provides a multi-parameter design method for engine rotor blade tips. This method involves performing composite deformation calculations on the rotor and rotor blades to obtain the rotor blade tip deformation, and then extracting the axial deformation at multiple points on the blade tip. The method also involves performing stator casing deformation calculations and extracting the deformation at the corresponding blade tip position in the casing. Based on the rotor and stator deformation, a diagram showing the relationship between the blade tip and casing in the operating state is drawn. Based on the diagram and the clearance requirements of engine operation, the final blade tip dimensions are determined segment by segment.

[0067] As described above, the multi-parameter design method for engine rotor blade tips of this invention introduces multi-point deformation at the rotor and stator blade tip positions when designing the blade tip clearance and shape, and determines the blade tip size segmentally based on the deformation. This effectively solves the problems of uneven blade tip deformation before and after deformation, resulting in some areas of scraping and some areas of excessive clearance. It ensures both safe engine operation and performance requirements. Furthermore, the improved design accuracy effectively reduces test iterations, shortens the cycle time, and reduces costs. This provides strong support for the safe and high-performance operation of aero engines.

[0068] The present invention also provides a multi-parameter design system for engine rotor blade tips, the design system employing the multi-parameter design method for engine rotor blade tips as described above, the design system comprising:

[0069] The blade tip simulation module is used to calculate the blade tip deformation, draw the desired blade tip thermal profile 200, and draw the final blade tip shape 400 based on the desired blade tip thermal profile 200 and the blade tip deformation.

[0070] The casing simulation module is used to measure the deformation of the computer casing and to draw the cold-state profile of the casing at 500.

[0071] The calculation module is used to determine the cold mounting clearance between the blade tip and the casing based on the cold profile 500 of the casing and the final shape 400 of the blade tip.

[0072] The present invention also provides an electronic device, including a processor and a memory, wherein the memory stores a program or instructions, and the processor executes the program or instructions, causing the electronic device to perform the multi-parameter design method for engine rotor blade tips as described above.

[0073] The present invention also provides a readable storage medium storing a program or instructions, wherein when the program or instructions are run on an electronic device, the electronic device executes the engine rotor blade tip multi-parameter design method as described above.

[0074] In summary, the multi-parameter design method for engine rotor blade tips of this invention is a multi-parameter, multi-objective blade tip design method that significantly improves the rationality of clearance design compared to traditional experience-based design methods. This invention's multi-parameter design method, system, and related devices for engine rotor blade tips introduce multi-point deformation at the rotor and stator blade tip positions when designing blade tip clearance and shape, and determine the blade tip size segmented according to the deformation. This method effectively solves the problems of uneven blade tip deformation before and after deformation, resulting in some areas of scraping and some areas of excessive clearance, ensuring both safe engine operation and performance requirements. Furthermore, the improved design accuracy effectively reduces experimental iterations, shortens the cycle time, and reduces costs. In addition, the proposed method clarifies the process, making the design process systematic, traceable, and repeatable.

[0075] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A multi-parameter design method for engine rotor blade tips, characterized in that, The design method includes the following steps: S1. Calculate the blade tip deformation and draw the blade tip thermal profile; S2. Draw the final shape of the blade tip based on the hot profile of the blade tip and the amount of deformation of the blade tip; S3, the deformation of the computer case, draw the cold-state profile of the case; S4. Determine the cold installation clearance between the blade tip and the casing based on the cold profile of the casing and the final shape of the blade tip.

2. The multi-parameter design method for engine rotor blade tips as described in claim 1, characterized in that, Step S1 includes the following steps: S 11 Perform composite calculations on the rotor and stator blades, and calculate the rotor blade tip deformation. S 12 1. Determine several axial positions of the rotor blade tip and extract the blade tip deformation; S 13 Set the hot design gap between the blade tip and the casing, and draw the hot profile of the blade tip based on the casing profile in operation.

3. The multi-parameter design method for engine rotor blade tips as described in claim 2, characterized in that, Step S 11 In the calculation, the rotor blade tip deformation is calculated using the finite element method. The rim deformation is determined by two-dimensional calculation, and the change of the blade tip relative to the rim is determined by three-dimensional calculation. The rotor blade tip deformation is obtained by superimposing the rim deformation and the change of the blade tip relative to the rim.

4. The multi-parameter design method for engine rotor blade tips as described in claim 2, characterized in that, Step S 12 Includes the following steps: S 121 Based on the uniform selection of blade width along the axial direction, determine several axial positions P1, P2...Pn of the rotor blade tip; S 122 Extract the axial deformation of multiple points δ1, δ2…δn at the blade tip; The blade tip deformation is defined as the multi-point deformation δ1, δ2…δn along the blade tip axis.

5. The multi-parameter design method for engine rotor blade tips as described in claim 1, characterized in that, Step S2 includes the following steps: S 21 Based on the hot profile of the blade tip and the amount of blade tip deformation, draw the cold profile of the blade tip; S 22 Based on the cold profile of the leaf tip, perform multi-segment linear fitting of the leaf tip to draw the final shape of the leaf tip.

6. The multi-parameter design method for engine rotor blade tips as described in claim 1, characterized in that, Step S3 includes the following steps: S 31 1. Conduct deformation calculations of the stator casing, determine several axial positions of the casing, and extract the deformation amount of the casing; S 32 Based on the casing profile in its operating state, and according to the deformation of the casing, the casing profile in its cold state is drawn.

7. The multi-parameter design method for engine rotor blade tips as described in claim 6, characterized in that, Step S 31 Includes the following steps: S 311 1. Select uniformly along the axial direction of the casing to determine several axial positions N1, N2...Nn of the casing; S 312 Extract the axial deformation of the casing at multiple points Δ1, Δ2…Δn; The deformation of the casing is expressed as the axial multi-point deformation Δ1, Δ2...Δn of the casing.

8. A multi-parameter design system for engine rotor blade tips, characterized in that, The design system employs the multi-parameter design method for engine rotor blade tips as described in any one of claims 1-7, and the design system includes: The blade tip simulation module is used to calculate the blade tip deformation, draw the blade tip thermal profile, and draw the final shape of the blade tip based on the blade tip thermal profile and the blade tip deformation. The casing simulation module is used to measure the deformation of the computer casing and to draw the cold-state profile of the casing. The calculation module is used to determine the cold installation clearance between the blade tip and the casing based on the cold profile of the casing and the final shape of the blade tip.

9. An electronic device, characterized in that, It includes a processor and a memory, the memory storing programs or instructions, the processor executing the programs or instructions to cause the electronic device to perform the engine rotor tip multi-parameter design method as described in any one of claims 1-7.

10. A readable storage medium, characterized in that, The readable storage medium stores a program or instructions, which, when executed on an electronic device, perform the engine rotor tip multi-parameter design method as described in any one of claims 1-7.

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