A method and system for designing a steady state clearance based on rotor tip penetration

Abstract

The present application relates to the technical field of aero-engine, and discloses a steady gap design method and system based on rotor tip intrusion, which obtains rotor tip intrusion of aero-engine in multiple working conditions, such as stable working state, overload working state and transition working state, and then analyzes the three types of rotor tip intrusion under each working condition to obtain the cold state gap of the rotor tip, so as to obtain the steady gap of each working condition; the absolute value of the steady gap difference of two preset examination working conditions is less than or equal to the preset deviation threshold, which is used as the design basis; the structure or working condition of the aero-engine is adjusted to realize the steady gap optimization design, and ensure that the absolute value of the steady gap difference of the two examination working conditions does not exceed the preset deviation threshold. The present application can realize reasonable matching of the tip gap under all working conditions, effectively reduce the aerodynamic leakage loss, improve the aerodynamic efficiency of the engine, avoid the safety risk of tip and casing friction, and reduce the research and development cost and shorten the development cycle.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology and discloses a steady-state clearance design method and system based on rotor blade tip intrusion. Background Technology

[0002] With the ever-increasing performance requirements of modern aircraft for aero-engines, the impact of variations in compressor and turbine blade tip clearance on engine performance is receiving increasing attention from engine designers. Excessive tip clearance leads to working medium leakage, causing efficiency losses and decreased engine performance; conversely, insufficient clearance can cause blade tip rubbing against the casing, inducing vibrations and seriously endangering engine safety, even leading to catastrophic accidents. Studies have shown that reducing tip clearance improves engine component efficiency and significantly reduces fuel consumption. Therefore, tip clearance control has always been a key area of ​​value exploration in aero-engine engineering applications.

[0003] Domestic and international scholars have conducted extensive fundamental research on aero-engine tip clearance control systems, aiming to further improve the overall efficiency of engines. Generally, the research focuses on two main aspects: first, studying the impact of tip clearance on component and overall efficiency, obtaining the aerodynamic efficiency variation law by changing the tip clearance and tip shape, and providing design targets for the clearance control system; second, conducting integrated application research on tip clearance control systems, mainly divided into passive control and active control. Passive control mainly includes sealing layer design methods and methods for controlling the opening of airflow path valves based on rotational speed. For example, honeycomb sealing is widely used, its function being to prevent gas leakage at the turbine tip by scraping the sealing layer. In the field of active clearance control, thermal control is a widely accepted method. Specifically, it involves setting up bleed air ducts to control the cooling airflow to exchange heat with the turbine casing, changing the temperature to change the expansion of the turbine casing, and thus further adjusting the clearance size.

[0004] For example, patent document CN108661723A discloses a turbine performance test specimen casing structure that can actively control the blade tip clearance, including a turbine casing, an intermediate casing, and a turbine outer ring. The intermediate casing is supplied with air by an air supply pipe and exhausts air by an exhaust pipe, so that the temperature of the intermediate casing is changed by supplying hot or cold air to the intermediate casing, causing the intermediate casing to expand or contract thermally. The intermediate casing drives the turbine outer ring hanging on it to move radially to change the blade tip clearance.

[0005] Besides controlling the tip clearance to reduce leakage losses, there are also methods to directly reduce leakage by optimizing the blade and casing structure. For example, an axial arc curve can be introduced into the original flat casing of the blade cascade, causing the casing to arch upwards and form an axisymmetric casing groove. At the same time, the geometric profile of the blade tip in the axisymmetric plane is kept at the same clearance size as the casing. This forms the arc shape of the rotor blade tip, with the blade tip extending into the casing groove. Numerical simulations show that, compared to traditional casings, the concave casing design can significantly reduce tip leakage flow losses by changing the pressure surface distribution at the turbine blade tip, with a maximum reduction of up to 6.1%.

[0006] These studies have revealed the impact of blade tip clearance on aerodynamic efficiency and provided specific clearance control system structures. However, in the initial stages of engine design, there is a lack of specific design methods for clearance control systems. The architecture of the clearance control system can only be determined through continuous trial and error and iteration after engine testing, which leads to serious problems such as a sharp increase in development cycle and cost. Summary of the Invention

[0007] The purpose of this invention is to provide a steady-state clearance design method and system based on rotor blade tip intrusion, which can achieve reasonable matching of blade tip clearance under all operating conditions, effectively reduce aerodynamic leakage losses, improve engine aerodynamic efficiency, and avoid the safety risks of blade tip rubbing against the casing.

[0008] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:

[0009] A steady-state clearance design method based on rotor blade tip intrusion includes: The rotor tip intrusion of the aero-engine under different operating conditions is obtained in the stable operating state, the rotor tip intrusion under the overload operating state, and the rotor tip intrusion under the transition operating state. The operating conditions include ground idle condition, ground takeoff condition, air slow cruise condition, air fast cruise condition, and maximum heat load condition. Based on the rotor blade tip intrusion amount under stable working conditions, rotor blade tip intrusion amount under overload working conditions, and rotor blade tip intrusion amount under transitional working conditions, the cold clearance of the rotor blade tip is obtained through analysis. Based on the cold clearance analysis of the obtained rotor blade tip, the steady-state clearance for each operating condition is obtained. If the absolute value of the difference between the steady-state clearances of two preset test operating conditions is greater than the preset deviation threshold, the structure or operating conditions of the aero-engine are adjusted until the absolute value of the difference between the steady-state clearances of the two preset test operating conditions is less than or equal to the preset deviation threshold.

[0010] Furthermore, the cold clearance at the rotor blade tip is based on Analysis yielded, among which This is the cold clearance at the rotor blade tip. For a given rotor tip clearance safety margin, for Rotor blade tip intrusion under stable operating conditions for Rotor blade tip intrusion under overload conditions for The amount of intrusion at the rotor blade tip during the transitional working state under operating conditions; The overload intrusion loading coefficient is the load factor. This indicates taking the maximum value among all operating conditions.

[0011] Furthermore, the overload intrusion loading coefficient The value is determined by the structure at the rotor blade tip clearance. If the corresponding stator is a rigid structure without coating or honeycomb, If the corresponding stator is a damage-resistant structure with a coating or honeycomb structure, ,in Pi It is a natural constant. For the thickness of the coating or honeycomb, The operating temperature for the coating or honeycomb structure.

[0012] Furthermore, the steady-state clearance under various operating conditions ,in This is the cold clearance at the rotor blade tip. for Rotor blade tip intrusion amount under stable operating conditions.

[0013] Furthermore, adjusting the structure or operating conditions of an aircraft engine includes one or more combinations of the following: Install a stator casing stiffness enhancement section; Install a stator casing thermal inertia enhancement section; Configure rotor disc thermal inertia adjustment holes; A flow area adjustment structure is installed for the rotor disc cooling system.

[0014] To achieve the above technical effects, the present invention also provides a steady-state clearance design system based on rotor tip intrusion, used to implement the aforementioned steady-state clearance design method based on rotor tip intrusion, comprising: The data acquisition module is used to acquire the rotor tip intrusion of the aero-engine under different operating conditions, including stable operation, overload operation, and transition operation. The operating conditions include ground idle operation, ground takeoff operation, slow cruise operation, fast cruise operation, and maximum heat load operation. The cold clearance analysis module is used to analyze and obtain the cold clearance of the rotor blade tip based on the rotor blade tip intrusion amount in the stable working state, the rotor blade tip intrusion amount in the overload working state, and the rotor blade tip intrusion amount in the transition working state under various operating conditions. The steady-state clearance determination module is used to obtain the steady-state clearance for each operating condition based on the cold clearance analysis of the rotor blade tip. If the absolute value of the difference between the steady-state clearances of two preset test operating conditions is greater than a preset deviation threshold, the structure or operating conditions of the aero-engine are adjusted until the absolute value of the difference between the steady-state clearances of the two preset test operating conditions is less than or equal to the preset deviation threshold.

[0015] Furthermore, in the cold clearance analysis module, the cold clearance at the rotor blade tip is determined according to... Analysis yielded, among which This is the cold clearance at the rotor blade tip. For a given rotor tip clearance safety margin, for Rotor blade tip intrusion under stable operating conditions for Rotor blade tip intrusion under overload conditions for The amount of intrusion at the rotor blade tip during the transitional working state under operating conditions; The overload intrusion loading coefficient is the load factor. This indicates taking the maximum value among all operating conditions.

[0016] Furthermore, in the cold gap analysis module, the overload intrusion loading coefficient... The value is determined by the structure at the rotor blade tip clearance. If the corresponding stator is a rigid structure without coating or honeycomb, If the corresponding stator is a damage-resistant structure with a coating or honeycomb structure, ,in Pi It is a natural constant. For the thickness of the coating or honeycomb, The operating temperature for the coating or honeycomb structure.

[0017] Furthermore, in the steady-state gap determination module, the steady-state gap for each operating condition... ,in This is the cold clearance at the rotor blade tip. for Rotor blade tip intrusion amount under stable operating conditions.

[0018] Compared with the prior art, the beneficial effects of this invention are: 1. This invention establishes a quantitative design process for blade tip clearance covering multiple operating conditions and working states. By using the absolute value of the steady-state clearance difference between two preset test conditions being less than or equal to a preset deviation threshold as the design basis, the structure or operating conditions of the aero-engine are adjusted to achieve steady-state clearance optimization design, ensuring that the absolute value of the steady-state clearance difference between the two test conditions does not exceed the preset deviation threshold.

[0019] 2. The steady-state clearance design method of the present invention fills the gap in the systematic design method of aero-engine blade tip clearance, changes the status quo of traditional blade tip clearance design relying on trial and error and lacking theoretical design basis, can achieve reasonable matching of blade tip clearance under all operating conditions, effectively reduce aerodynamic leakage loss, improve engine aerodynamic efficiency, avoid the safety risk of blade tip rubbing against casing, and reduce the number of physical tests, reduce R&D costs and shorten the development cycle. Attached Figure Description

[0020] Figure 1 This is a flowchart of the steady-state clearance design method based on rotor tip intrusion in the embodiment; Figure 2 This is a schematic diagram of the gap control system for active-passive fusion in the embodiment; Among them, 1. Stator casing stiffness enhancement section; 2. Stator casing thermal inertia enhancement section; 3. Rotor disc thermal inertia adjustment hole; 4. Flow area adjustment structure. Detailed Implementation

[0021] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0022] Example 1 See Figure 1 A steady-state clearance design method based on rotor blade tip intrusion includes: The rotor tip intrusion of the aero-engine under different operating conditions is obtained in the stable operating state, the rotor tip intrusion under the overload operating state, and the rotor tip intrusion under the transition operating state. The operating conditions include ground idle condition, ground takeoff condition, air slow cruise condition, air fast cruise condition, and maximum heat load condition. Based on the rotor blade tip intrusion amount under stable working conditions, rotor blade tip intrusion amount under overload working conditions, and rotor blade tip intrusion amount under transitional working conditions, the cold clearance of the rotor blade tip is obtained through analysis. Based on the cold clearance analysis of the obtained rotor blade tip, the steady-state clearance for each operating condition is obtained. If the absolute value of the difference between the steady-state clearances of two preset test operating conditions is greater than the preset deviation threshold, the structure or operating conditions of the aero-engine are adjusted until the absolute value of the difference between the steady-state clearances of the two preset test operating conditions is less than or equal to the preset deviation threshold.

[0023] In this embodiment, the rotor tip intrusion of the aero-engine is obtained under various operating conditions, including ground idle, ground takeoff, slow in-flight cruise, fast in-flight cruise, and maximum thermal load, as well as under stable, overload, and transitional operating conditions. The cold-state clearance of the rotor tip is then calculated based on the three types of rotor tip intrusion under each operating condition, thus obtaining the steady-state clearance for each condition. By using the absolute value of the steady-state clearance difference between two preset test conditions being less than or equal to a preset deviation threshold as the design basis, the steady-state clearance is optimized by adjusting the aero-engine's structure or operating conditions, ensuring that the absolute value of the steady-state clearance difference between the two test conditions does not exceed the preset deviation threshold. This method establishes a quantitative design process for blade tip clearance covering multiple operating conditions and states, filling the gap in systematic design methods for aero-engine blade tip clearance. It changes the traditional situation where blade tip clearance design relies on trial and error and lacks theoretical design basis. It can achieve reasonable matching of blade tip clearance under all operating conditions, effectively reducing aerodynamic leakage losses, improving engine aerodynamic efficiency, avoiding the safety risks of blade tip rubbing against the casing, reducing the number of physical tests, lowering R&D costs, and shortening the development cycle.

[0024] Based on the same inventive concept, this embodiment also provides a steady-state clearance design system based on rotor tip intrusion, used to implement the aforementioned steady-state clearance design method based on rotor tip intrusion, including: The data acquisition module is used to acquire the rotor tip intrusion of the aero-engine under different operating conditions, including stable operation, overload operation, and transition operation. The operating conditions include ground idle operation, ground takeoff operation, slow cruise operation, fast cruise operation, and maximum heat load operation. The cold clearance analysis module is used to analyze and obtain the cold clearance of the rotor blade tip based on the rotor blade tip intrusion amount in the stable working state, the rotor blade tip intrusion amount in the overload working state, and the rotor blade tip intrusion amount in the transition working state under various operating conditions. The steady-state clearance determination module is used to obtain the steady-state clearance for each operating condition based on the cold clearance analysis of the rotor blade tip. If the absolute value of the difference between the steady-state clearances of two preset test operating conditions is greater than a preset deviation threshold, the structure or operating conditions of the aero-engine are adjusted until the absolute value of the difference between the steady-state clearances of the two preset test operating conditions is less than or equal to the preset deviation threshold.

[0025] Example 2 See Figure 1 and Figure 2 A steady-state clearance design method based on rotor blade tip intrusion, characterized in that it includes: Step 1: Obtain the rotor tip intrusion of the aero-engine under different operating conditions, including stable operation, overload operation, and transition operation. The operating conditions include ground idle operation, ground takeoff operation, slow cruise operation, fast cruise operation, and maximum heat load operation. In this embodiment, the rotor blade tip intrusion amount under stable operating conditions ,in for Rotor blade tip intrusion under stable operating conditions for The amount of deformation at the rotor blade tip when the rotor is in a stable working state. This includes the centrifugal elongation and thermal elongation of the rotor; for The amount of stator deformation at the blade tip under stable operating conditions. This includes stator thermal deformation and constraint deformation.

[0026] Rotor tip intrusion under overload operating conditions ,in for Rotor blade tip intrusion under overload conditions for The amount of deformation at the rotor blade tip caused by normal overload under operating conditions. for Deformation of the rotor blade tip caused by yaw overload under operating conditions. for The amount of deformation at the rotor blade tip caused by pitch overload under operating conditions; It should be noted that overload operating conditions usually exist in ground takeoff and high-speed cruise conditions in the air; therefore, the rotor blade tip intrusion under overload operating conditions in other operating conditions is small and can be ignored, or it can be calculated using the above formula based on actual simulation or experimental data.

[0027] Rotor tip intrusion during transitional operating conditions ,in for The amount of intrusion at the rotor blade tip during the transitional working state under operating conditions. for Rotor deformation at the blade tip during transitional operating conditions. for The amount of stator deformation at the blade tip during transitional working conditions. for The amount of rotor deformation at the blade tip during the transitional working state under operating conditions.

[0028] Step 2: Based on the rotor tip intrusion amount in the stable working state, the rotor tip intrusion amount in the overload working state, and the rotor tip intrusion amount in the transition working state under each working condition, analyze and obtain the cold clearance of the rotor tip. In this embodiment, the cold clearance at the rotor blade tip is determined according to... Analysis yielded, among which This is the cold clearance at the rotor blade tip. Given the rotor tip clearance safety margin; for Rotor blade tip intrusion under stable operating conditions for Rotor blade tip intrusion under overload conditions for The amount of intrusion at the rotor blade tip during the transitional working state under operating conditions; The overload intrusion loading coefficient is the load factor. This indicates taking the maximum value among all operating conditions.

[0029] In this embodiment, the overload intrusion loading coefficient The value is determined by the structure at the rotor blade tip clearance. If the corresponding stator is a rigid structure without coating or honeycomb, If the corresponding stator is a damage-resistant structure with a coating or honeycomb structure, ,in Pi It is a natural constant. For the thickness of the coating or honeycomb, The operating temperature for the coating or honeycomb structure.

[0030] Step 3: Based on the cold clearance analysis of the rotor blade tip, obtain the steady-state clearance for each operating condition. If the absolute value of the difference between the steady-state clearances of two preset test operating conditions is greater than the preset deviation threshold, then adjust the structure or operating conditions of the aero-engine until the absolute value of the difference between the steady-state clearances of the two preset test operating conditions is less than or equal to the preset deviation threshold. In this embodiment, the steady-state clearance under each operating condition is... Calculations are performed by substituting the corresponding temperature and honeycomb thickness. , Relevant data for each working condition and As shown in Table 1: Table 1. Statistical table of relevant data values ​​under different working conditions (unit: mm)

[0031] In this embodiment, the ground takeoff condition and the slow-speed cruise condition are identified as the two main operating conditions. The passability is considered satisfactory when the steady-state clearance difference between these two main operating conditions is no greater than 0.05% of the rotor blade height, and the steady-state clearance design is complete. Otherwise, steady-state clearance adjustment is required until the difference between the steady-state clearances of the two main operating conditions is no greater than 0.05% of the rotor blade height. According to the relevant data in Table 1, the steady-state clearance difference between the ground takeoff condition and the slow-speed cruise condition is 0.5 mm, exceeding the 0.3 mm corresponding to 0.05% of the blade height; therefore, steady-state clearance adjustment is necessary.

[0032] In some embodiments, the specific adjustment process can employ a gap control system that integrates active and passive mechanisms, specifically including the following methods: The design of the gap passive control includes: 1) High-strength materials and high-rigidity rotor structure design are adopted to reduce rotor tip intrusion under overload conditions. .

[0033] 2) Match the rotor-stator thermal inertia time constant and the rotor-stator material thermal expansion coefficient to determine the rotor tip intrusion amount during transitional operation. .

[0034] 3) Employing materials with low thermal expansion coefficients and high rigidity design reduces stator deformation under specific operating conditions, thereby increasing rotor tip intrusion during stable operation under those specific conditions. .

[0035] In this embodiment, passive clearance control is achieved by setting a stator casing stiffness enhancement section 1, a stator casing thermal inertia enhancement section 2, and a rotor disc thermal inertia adjustment hole 3. Specifically, by analyzing the deformation characteristics of the stator casing, circumferential or longitudinal reinforcing ribs are set as stator casing stiffness enhancement sections 1 in areas with weak bending resistance of the stator casing. This increases the interface moment of inertia, enhances the stator casing stiffness, and optimizes stator deformation, thereby reducing the steady-state rotor intrusion and the rotor tip intrusion under overload conditions. By analyzing the rotor-stator transition deformation law, a circular protrusion structure is set on the stator casing as a stator casing thermal inertia enhancement section 2. This increases the thermal inertia time constant of the stator casing, improves the casing heat capacity, and aims to change the stator heat capacity and match the rotor-stator transition thermal inertia. Furthermore, the rotor disc thermal inertia adjustment hole 3 is used for bleed air, which can reduce the rotor disc thermal inertia time constant.

[0036] Furthermore, in some other embodiments, after adjusting the matching of the stator casing thermal inertia enhancement section 2 and the rotor wheel disk thermal inertia adjustment hole 3, the rotor blade tip intrusion during the transitional operating state can be further reduced.

[0037] The active clearance control design includes: By adopting an active temperature regulation method, the stator temperature under specific operating conditions is reduced, while the rotor temperature under the same specific operating conditions is increased.

[0038] For example, in this embodiment, a rotor disk cooling system flow area adjustment structure 4 is provided, which is driven by the engine control system to adjust the cooling system flow area under slow-speed cruise conditions in the air, change the temperature of the rotor disk, and achieve the effect of adjusting the steady-state gap difference value between slow-speed cruise conditions in the air and ground takeoff conditions.

[0039] The adjusted test data and calculation results for this embodiment are shown in Table 2 below: Table 2. Statistical table of relevant data values ​​for different working conditions after adjustment (unit: mm)

[0040] The above data shows that through active and passive integrated control, both structural optimization (such as reinforced sections and adjustment holes) is used to improve basic performance, and adjustable mechanisms (such as flow area adjustment) are introduced to cope with dynamic operating conditions. The steady-state clearance difference is reduced, so that the blade tip clearance can be kept optimal under various flight conditions, thereby effectively reducing aerodynamic leakage loss, improving engine efficiency, and avoiding the risk of blade tip rubbing.

[0041] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A steady-state clearance design method based on rotor blade tip intrusion, characterized in that, include: The rotor tip intrusion of the aero-engine under different operating conditions is obtained in the stable operating state, the rotor tip intrusion under the overload operating state, and the rotor tip intrusion under the transition operating state. The operating conditions include ground idle condition, ground takeoff condition, air slow cruise condition, air fast cruise condition, and maximum heat load condition. Based on the rotor tip intrusion under stable operating conditions, overload operating conditions, and transition operating conditions, the cold clearance of the rotor tip is analyzed and obtained. The cold clearance of the rotor tip is determined according to... Analysis yielded, among which This is the cold clearance at the rotor blade tip. For a given rotor tip clearance safety margin, for Rotor blade tip intrusion under stable operating conditions for Rotor blade tip intrusion under overload conditions for The amount of intrusion at the rotor blade tip during the transitional working state under operating conditions; The overload intrusion loading coefficient is the overload intrusion loading coefficient. The value is determined by the structure at the rotor blade tip clearance. If the corresponding stator is a rigid structure without coating or honeycomb, If the corresponding stator is a damage-resistant structure with a coating or honeycomb structure, ,in Pi It is a natural constant. The thickness of the coating or honeycomb. The operating temperature for the coating or honeycomb structure. This indicates taking the maximum value among all operating conditions; Based on the cold clearance analysis of the obtained rotor blade tip, the steady-state clearance for each operating condition is obtained. If the absolute value of the difference between the steady-state clearances of two preset test operating conditions is greater than the preset deviation threshold, the structure or operating conditions of the aero-engine are adjusted until the absolute value of the difference between the steady-state clearances of the two preset test operating conditions is less than or equal to the preset deviation threshold.

2. The steady-state clearance design method based on rotor tip intrusion as described in claim 1, characterized in that, Steady-state clearance under various operating conditions ,in This is the cold clearance at the rotor blade tip. for Rotor blade tip intrusion amount under stable operating conditions.

3. The steady-state clearance design method based on rotor tip intrusion as described in claim 1, characterized in that, Adjusting the structure or operating conditions of an aircraft engine includes one or more combinations of the following: Install a stator casing stiffness enhancement section; Install a stator casing thermal inertia enhancement section; Configure rotor disc thermal inertia adjustment holes; A flow area adjustment structure is installed for the rotor disc cooling system.

4. A steady-state clearance design system based on rotor tip intrusion, used to implement the steady-state clearance design method based on rotor tip intrusion as described in any one of claims 1 to 3, characterized in that, include: The data acquisition module is used to acquire the rotor tip intrusion of the aero-engine under different operating conditions, including stable operation, overload operation, and transition operation. The operating conditions include ground idle operation, ground takeoff operation, slow cruise operation, fast cruise operation, and maximum heat load operation. The cold clearance analysis module is used to analyze and obtain the cold clearance of the rotor blade tip based on the rotor blade tip intrusion amount in the stable working state, the rotor blade tip intrusion amount in the overload working state, and the rotor blade tip intrusion amount in the transition working state under various operating conditions. The steady-state clearance determination module is used to obtain the steady-state clearance for each operating condition based on the cold clearance analysis of the rotor blade tip. If the absolute value of the difference between the steady-state clearances of two preset test operating conditions is greater than a preset deviation threshold, the structure or operating conditions of the aero-engine are adjusted until the absolute value of the difference between the steady-state clearances of the two preset test operating conditions is less than or equal to the preset deviation threshold.

5. The steady-state clearance design system based on rotor tip intrusion as described in claim 4, characterized in that, In the cold clearance analysis module, the cold clearance at the rotor blade tip is determined according to... Analysis yielded, among which This is the cold clearance at the rotor blade tip. For a given rotor tip clearance safety margin, for Rotor blade tip intrusion under stable operating conditions for Rotor blade tip intrusion under overload conditions for The amount of intrusion at the rotor blade tip during the transitional working state under operating conditions; The overload intrusion loading coefficient is the load factor. This indicates taking the maximum value among all operating conditions.

6. The steady-state clearance design system based on rotor tip intrusion as described in claim 5, characterized in that, In the cold gap analysis module, the overload intrusion loading coefficient The value is determined by the structure at the rotor blade tip clearance. If the corresponding stator is a rigid structure without coating or honeycomb, If the corresponding stator is a damage-resistant structure with a coating or honeycomb structure, ,in Pi It is a natural constant. The thickness of the coating or honeycomb. The operating temperature for the coating or honeycomb structure.

7. The steady-state clearance design system based on rotor tip intrusion as described in claim 4, characterized in that, In the steady-state gap determination module, the steady-state gap for each operating condition is... ,in This is the cold clearance at the rotor blade tip. for Rotor blade tip intrusion amount under stable operating conditions.

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