A design method and system for self-circulation passive stability expansion of a multi-stage axial flow compressor
By using CFD numerical simulation and structural optimization of the self-circulating casing, the problem of lack of systematic methods in the design of the self-circulating casing was solved. This enabled the improvement of stability margin and maintenance of aerodynamic efficiency of the multi-stage axial compressor across the entire speed range, meeting the design requirements of high stability margin and high efficiency for aero engines.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AECC SICHUAN GAS TURBINE RES INST
- Filing Date
- 2026-06-11
- Publication Date
- 2026-07-10
AI Technical Summary
The existing self-circulating casing processing structure design lacks a systematic approach, resulting in long development cycles, difficulty in adapting to different models and aerodynamic loads, inability to simultaneously improve the stability margin and aerodynamic efficiency of multi-stage axial compressors, and inability to meet the design requirements of modern aero engines for high stability margin and high efficiency.
By establishing a CFD numerical simulation model of a multi-stage axial compressor, aerodynamic performance calculations and stability analysis are performed to determine the stall first stage. A self-circulating channel is opened in the casing corresponding to the rotor blades of the first stage, and the position and size of the nozzle and extraction port are optimized to form a self-circulating casing treatment structure, ensuring an increase in stability margin across the entire speed range.
It achieves an increase in the stability margin of multi-stage axial compressors across the entire speed range, meeting the stability margin requirements of aero engines, avoiding the problem of insufficient stability margin in the high-load operating range, while maintaining aerodynamic efficiency.
Smart Images
Figure CN122365732A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aerodynamic design technology for multi-stage axial compressors, and discloses a design method and system for a self-circulating passive expansion and stabilization of a multi-stage axial compressor. Background Technology
[0002] Aircraft place increasingly stringent demands on their power systems, and high performance has always been a relentless pursuit for aero-engines. The multi-stage axial compressor is a core component of an aero-engine, and its performance has a decisive impact on many engine performance parameters, particularly efficiency and operating limits. The high-performance design requirements of aero-engines have led to continuously increasing aerodynamic loads on individual compressor stages. High maneuverability and complex, variable operating conditions make it easier for compressors to exceed stable operating limits and enter the flow stall region, posing a serious threat to the safety of multi-stage compressors and even the entire aero-engine.
[0003] Casing treatment, as a passive flow control method, is widely used in the tip flow control of multi-stage compressors for aerodynamic stabilization. Casing treatment serves two main purposes: first, it reduces the aerodynamic load at the tip, thereby decreasing the driving force of the tip leakage flow and suppressing tip blockage caused by tip leakage vortices; second, it acts as a flow straightener, suppressing tip blockage through airflow circulation within slots or grooves. However, traditional casing treatments such as circumferential slots, axial slots, and inclined slots, while expanding stability, reduce the aerodynamic efficiency of multi-stage axial compressors, and the stability margin of multi-stage compressors cannot be improved across the entire operating speed range. These drawbacks limit the engineering application of casing treatment technology in the field of aerodynamic stabilization of aero-engine compressors. Self-circulating casing treatment technology utilizes the pressure difference before and after the compressor to draw in high-pressure gas from the rotor trailing edge and inject it into the leading edge of the rotor blade tip. This allows the low-energy fluid at the rotor tip to gain additional kinetic energy, improving flow blockage at the rotor tip and thus enhancing the stability margin of the multi-stage compressor. The self-circulating casing process does not rely on an additional power unit. It uses the pressure difference before and after the compressor to form natural suction and injection, thereby improving the unstable flow at the rotor blade tip and expanding the stability margin and operating range of the multi-stage axial compressor.
[0004] However, the design of existing self-circulating casing handling structures mainly relies on the experience of designers for trial and error, lacking systematic design method guidance. This not only results in long development cycles but also makes it difficult to adapt to the actual flow requirements of multi-stage axial compressors of different models and aerodynamic loads. Some structural designs may even fail to effectively improve stability margin due to unreasonable matching of the position and flow area of the suction port and the injection port, and cause a significant drop in aerodynamic efficiency under rated operating conditions of the compressor. It is difficult to balance stability enhancement and aerodynamic efficiency, and cannot meet the design requirements of modern aero engines for compressors that simultaneously pursue high stability margin and high efficiency. Summary of the Invention
[0005] The purpose of this invention is to provide a design method and system for a self-circulating passive stability enhancement of a multi-stage axial compressor, which can ensure the increase of stability margin of the multi-stage axial compressor across the entire speed range, thereby meeting the engine's requirements for the stability margin of the multi-stage axial compressor and avoiding the problem of insufficient stability margin of the high-load multi-stage axial compressor across the entire operating speed range.
[0006] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:
[0007] A design method for a self-circulating passive stabilization multi-stage axial compressor includes: Based on the aerodynamic modeling data of the multi-stage axial compressor, a CFD numerical simulation model of the multi-stage axial compressor is established. The aerodynamic performance of the multi-stage axial compressor is calculated over the entire speed range, and the aerodynamic performance parameters of the multi-stage axial compressor over the entire speed range are obtained. The aerodynamic performance parameters include flow rate, total pressure ratio, and efficiency. Based on the obtained aerodynamic performance parameters, stability analysis of the engine under different operating conditions is carried out to obtain the minimum stability margin operating condition N of the engine with a stability margin less than the preset margin value. For operating condition N, based on the CFD numerical simulation model of the multi-stage axial compressor, unsteady calculation boundary conditions are applied to carry out unsteady flow field calculation of the multi-stage axial compressor under operating condition N, and the first stage of stall of the multi-stage axial compressor is determined. If the first stage of a multi-stage axial compressor stalls is a rotor blade, and the stall location is at the blade tip, then a self-circulating channel is opened in the compressor casing corresponding to the first stage rotor blade to form a self-circulating casing treatment structure; the self-circulating casing treatment structure consists of a nozzle, an extraction port, and a self-circulating channel. Using the position and size parameters of the self-circulating casing treatment structure as design variables, the CFD method is used to calculate the aerodynamic performance of a multi-stage axial compressor with a self-circulating casing treatment structure under different design variables and to analyze the engine's stability under N conditions. The dimensions of the self-circulating casing treatment structure that meet or exceed the preset margin value are obtained, and the design of the self-circulating casing treatment structure is completed.
[0008] Furthermore, if the first stage of stall in the multi-stage axial compressor is a stator blade, or if the stall location is not at the tip of the rotor blade, then the aerodynamic modeling data of the multi-stage axial compressor is adjusted until the stability margin of the engine under N conditions is greater than or equal to the preset margin value.
[0009] Furthermore, the blade tip is the region that is 20% of the blade height from the blade tip of the rotor blade.
[0010] Furthermore, the position of the self-circulating casing processing structure includes the nozzle position and the suction port position, and the dimensional parameters of the self-circulating casing processing structure include the nozzle aspect ratio, the suction angle, and the suction port aspect ratio.
[0011] To achieve the above technical effects, the present invention also provides a design system for a self-circulating passive stabilization of a multi-stage axial compressor, used to implement the aforementioned design method for a self-circulating passive stabilization of a multi-stage axial compressor, comprising: The aerodynamic simulation module is used to establish a CFD numerical simulation model of a multi-stage axial compressor based on the aerodynamic modeling data of the multi-stage axial compressor, perform aerodynamic performance calculations of the multi-stage axial compressor across the entire speed range, and obtain aerodynamic performance parameters of the multi-stage axial compressor across the entire speed range, including flow rate, total pressure ratio, and efficiency. The stability analysis module is used to conduct stability analysis of the engine under different operating conditions based on the acquired aerodynamic performance parameters, and to obtain the minimum stability margin operating condition N of the engine with a stability margin less than a preset margin value. The unsteady analysis module is used to apply unsteady calculation boundary conditions to the CFD numerical simulation model of the multi-stage axial compressor, carry out unsteady flow field calculation of the multi-stage axial compressor under operating condition N, and determine the first stage of stall of the multi-stage axial compressor. The discrimination and processing module is used to open a self-circulation channel in the compressor casing corresponding to the rotor blade of the first stage when the stall of the multi-stage axial compressor is a rotor blade and the stall position is located at the blade tip, so as to form a self-circulation casing processing structure; the self-circulation casing processing structure consists of a nozzle, an extraction port and a self-circulation channel. The adjustment and optimization module is used to calculate the aerodynamic performance of a multi-stage axial compressor with a self-circulating casing treatment structure and perform engine stability analysis under N conditions using CFD methods, with the position and size parameters of the self-circulating casing treatment structure as design variables. The module obtains the dimensions of the self-circulating casing treatment structure that meet or exceed the preset margin value, and completes the design of the self-circulating casing treatment structure.
[0012] Furthermore, in the discrimination processing module, if the first stage of stall of the multi-stage axial compressor is a stator blade, or the stall position is not at the tip of the rotor blade, the aerodynamic modeling data of the multi-stage axial compressor is adjusted until the stability margin of the engine under N condition is greater than or equal to the preset margin value.
[0013] Furthermore, in the discrimination processing module, the blade tip is the region that is 20% of the blade height from the blade tip of the rotor blade.
[0014] Furthermore, in the adjustment and optimization module, the position of the self-circulating casing processing structure includes the nozzle position and the suction port position, and the dimensional parameters of the self-circulating casing processing structure include the nozzle aspect ratio, the suction angle, and the suction port aspect ratio.
[0015] Compared with existing technologies, the beneficial effects of this invention are as follows: This invention obtains the operating condition of insufficient stability margin of multi-stage axial compressors through aerodynamic performance calculation and engine stability assessment; it conducts unsteady flow field simulation of the insufficient stability margin condition of multi-stage axial compressors to determine the first stage stall. For the first stage rotor tip stall, a self-circulating casing is used to passively extend the stability of the multi-stage compressor; and based on the sensitivity analysis of the self-circulating casing design parameters, the optimal design parameters of the self-circulating casing are selected to ensure an increase in the stability margin of the multi-stage axial compressor across the entire speed range, thereby meeting the stability margin requirements of multi-stage axial compressors and avoiding the problem of insufficient stability margin of high-load multi-stage axial compressors across the entire operating speed range. Attached Figure Description
[0016] Figure 1 Example 1: Flowchart of the design method for the self-circulating passive stabilization of a multi-stage axial compressor; Figure 2 This is a block diagram of the self-circulating passive stabilization design system of the multi-stage axial compressor in Example 1; Figure 3 This is a flowchart of the design method for the self-circulating passive stabilization of the multi-stage axial compressor in Example 2; The module includes: 1. Aerodynamic simulation module; 2. Stability analysis module; 3. Unsteady analysis module; 4. Judgment and processing module; and 5. Adjustment and optimization module. Detailed Implementation
[0017] 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.
[0018] Example 1 See Figure 1 and Figure 2 A design method for a self-circulating passive stabilization expansion of a multi-stage axial compressor, comprising: Based on the aerodynamic modeling data of the multi-stage axial compressor, a CFD numerical simulation model of the multi-stage axial compressor is established. The aerodynamic performance of the multi-stage axial compressor is calculated over the entire speed range, and the aerodynamic performance parameters of the multi-stage axial compressor over the entire speed range are obtained. The aerodynamic performance parameters include flow rate, total pressure ratio, and efficiency. Based on the obtained aerodynamic performance parameters, stability analysis of the engine under different operating conditions is carried out to obtain the minimum stability margin operating condition N of the engine with a stability margin less than the preset margin value. For operating condition N, based on the CFD numerical simulation model of the multi-stage axial compressor, unsteady calculation boundary conditions are applied to carry out unsteady flow field calculation of the multi-stage axial compressor under operating condition N, and the first stage of stall of the multi-stage axial compressor is determined. If the first stage of a multi-stage axial compressor stalls is a rotor blade, and the stall location is at the blade tip, then a self-circulating channel is opened in the compressor casing corresponding to the first stage rotor blade to form a self-circulating casing treatment structure; the self-circulating casing treatment structure consists of a nozzle, an extraction port, and a self-circulating channel. Using the position and size parameters of the self-circulating casing treatment structure as design variables, the CFD method is used to calculate the aerodynamic performance of a multi-stage axial compressor with a self-circulating casing treatment structure under different design variables and to analyze the engine's stability under N conditions. The dimensions of the self-circulating casing treatment structure that meet or exceed the preset margin value are obtained, and the design of the self-circulating casing treatment structure is completed.
[0019] In this embodiment, the insufficient stability margin of the multi-stage axial compressor is obtained through aerodynamic performance calculations and engine stability assessments. Unsteady flow field simulations under this condition are conducted to determine the first stage stall. For the first stage rotor tip stall, a self-circulating casing is used to passively extend the stability of the multi-stage compressor. Furthermore, the self-circulating casing structure is derived from the sensitivity analysis of its design parameters relative to the insufficient stability margin condition, obtaining the optimal design parameters to ensure an increase in the stability margin of the multi-stage axial compressor across the entire speed range. This satisfies the stability margin requirements of the multi-stage axial compressor and avoids the problem of insufficient stability margin in high-load multi-stage axial compressors across the entire operating speed range.
[0020] Based on the same inventive concept, this embodiment also provides a design system for a multi-stage axial compressor with self-circulation passive stabilization, used to implement the aforementioned design method for a multi-stage axial compressor with self-circulation passive stabilization, including: The aerodynamic simulation module 1 is used to establish a CFD numerical simulation model of the multi-stage axial compressor based on the aerodynamic modeling data of the multi-stage axial compressor, perform aerodynamic performance calculations of the multi-stage axial compressor across the entire speed range, and obtain aerodynamic performance parameters of the multi-stage axial compressor across the entire speed range, including flow rate, total pressure ratio, and efficiency. Stability analysis module 2 is used to conduct stability analysis of the engine under different operating conditions based on the acquired aerodynamic performance parameters, and to obtain the minimum stability margin operating condition N of the engine with a stability margin less than a preset margin value. Unsteady analysis module 3 is used to apply unsteady calculation boundary conditions to the CFD numerical simulation model of the multi-stage axial compressor, carry out unsteady flow field calculation of the multi-stage axial compressor under operating condition N, and determine the first stage of stall of the multi-stage axial compressor. The discrimination and processing module 4 is used to open a self-circulation channel in the compressor casing corresponding to the rotor blade of the first stage when the stall of the multi-stage axial compressor is a rotor blade and the stall position is located at the blade tip, so as to form a self-circulation casing processing structure; the self-circulation casing processing structure consists of a nozzle, an extraction port and a self-circulation channel. The adjustment and optimization module 5 is used to calculate the aerodynamic performance of a multi-stage axial compressor with a self-circulating casing treatment structure and analyze the engine's stability under N conditions using CFD methods, with the position and size parameters of the self-circulating casing treatment structure as design variables. The module obtains the dimensions of the self-circulating casing treatment structure that meet or exceed the preset margin value, and completes the design of the self-circulating casing treatment structure.
[0021] Example 2 See Figure 3 A design method for a self-circulating passive stabilization expansion of a multi-stage axial compressor, comprising: Step 1: Based on the aerodynamic modeling data of the multi-stage axial compressor, establish a CFD numerical simulation model of the multi-stage axial compressor, perform aerodynamic performance calculations of the multi-stage axial compressor across the entire speed range, and obtain the aerodynamic performance parameters of the multi-stage axial compressor across the entire speed range, including flow rate, total pressure ratio, and efficiency.
[0022] Step 2: Based on the obtained aerodynamic performance parameters, conduct stability analysis of the engine under different operating conditions to obtain the minimum stability margin operating condition N of the engine with a stability margin less than the preset margin value.
[0023] Step 3: For operating condition N, based on the CFD numerical simulation model of the multi-stage axial compressor, apply unsteady calculation boundary conditions, carry out unsteady flow field calculation of the multi-stage axial compressor under operating condition N, and determine the first stage of stall of the multi-stage axial compressor.
[0024] Step 4: If the stall of the first stage of the multi-stage axial compressor is a rotor blade and the stall location is at the blade tip, then a self-circulating channel is opened in the compressor casing corresponding to the rotor blade of the first stage to form a self-circulating casing treatment structure, and then proceed to step 5; otherwise, proceed to step 6. The self-circulating casing processing structure in this embodiment consists of a nozzle, an extraction port, and a self-circulating channel; the blade tip is the region 20% of the blade height from the blade tip of the rotor blade.
[0025] Step 5: Using the position and size parameters of the self-circulating casing treatment structure as design variables, the CFD method is used to calculate the aerodynamic performance of the multi-stage axial compressor with the self-circulating casing treatment structure under different design variables and to analyze the stability of the engine under N conditions. The size of the self-circulating casing treatment structure that meets the preset margin value is obtained, and the design of the self-circulating casing treatment structure is completed. The location of the self-circulating casing processing structure includes the nozzle location and the suction port location, and the dimensional parameters of the self-circulating casing processing structure include the nozzle aspect ratio, suction angle, and suction port aspect ratio.
[0026] Step 6: If the stall of the multi-stage axial compressor is caused by a stator blade, or if the stall location is not at the tip of a rotor blade, adjust the aerodynamic modeling data of the multi-stage axial compressor until the stability margin of the engine under N conditions is greater than or equal to the preset margin value.
[0027] 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 design method for a self-circulating passive stabilization expansion and stabilization of a multi-stage axial flow compressor, characterized in that, include: Based on the aerodynamic modeling data of the multi-stage axial compressor, a CFD numerical simulation model of the multi-stage axial compressor is established. The aerodynamic performance of the multi-stage axial compressor is calculated over the entire speed range, and the aerodynamic performance parameters of the multi-stage axial compressor over the entire speed range are obtained. The aerodynamic performance parameters include flow rate, total pressure ratio, and efficiency. Based on the obtained aerodynamic performance parameters, stability analysis of the engine under different operating conditions is carried out to obtain the minimum stability margin operating condition N of the engine with a stability margin less than the preset margin value. For operating condition N, based on the CFD numerical simulation model of the multi-stage axial compressor, unsteady calculation boundary conditions are applied to carry out unsteady flow field calculation of the multi-stage axial compressor under operating condition N, and the first stage of stall of the multi-stage axial compressor is determined. If the first stage of a multi-stage axial compressor stalls is a rotor blade, and the stall location is at the blade tip, then a self-circulating channel is opened in the compressor casing corresponding to the first stage rotor blade to form a self-circulating casing treatment structure; the self-circulating casing treatment structure consists of a nozzle, an extraction port, and a self-circulating channel. Using the position and size parameters of the self-circulating casing treatment structure as design variables, the CFD method is used to calculate the aerodynamic performance of a multi-stage axial compressor with a self-circulating casing treatment structure under different design variables and to analyze the engine's stability under N conditions. The dimensions of the self-circulating casing treatment structure that meet or exceed the preset margin value are obtained, and the design of the self-circulating casing treatment structure is completed.
2. The design method for self-circulating passive stabilization of a multi-stage axial compressor according to claim 1, characterized in that, If the stall of the multi-stage axial compressor is caused by a stator blade in the first stage, or if the stall location is not at the tip of a rotor blade, then adjust the aerodynamic modeling data of the multi-stage axial compressor until the stability margin of the engine under N conditions is greater than or equal to the preset margin value.
3. The design method for self-circulating passive stabilization of a multi-stage axial compressor according to claim 1, characterized in that, The blade tip is the area 20% of the blade height from the blade tip of the rotor blade.
4. The design method for self-circulating passive stabilization of a multi-stage axial compressor according to claim 1, characterized in that, The location of the self-circulating casing processing structure includes the nozzle position and the suction port position, and the dimensional parameters of the self-circulating casing processing structure include the nozzle aspect ratio, suction angle, and suction port aspect ratio.
5. A design system for a self-circulating passive stabilization of a multi-stage axial compressor, used to implement the design method for a self-circulating passive stabilization of a multi-stage axial compressor as described in claim 1, characterized in that, include: The aerodynamic simulation module is used to establish a CFD numerical simulation model of a multi-stage axial compressor based on the aerodynamic modeling data of the multi-stage axial compressor, perform aerodynamic performance calculations of the multi-stage axial compressor across the entire speed range, and obtain aerodynamic performance parameters of the multi-stage axial compressor across the entire speed range, including flow rate, total pressure ratio, and efficiency. The stability analysis module is used to conduct stability analysis of the engine under different operating conditions based on the acquired aerodynamic performance parameters, and to obtain the minimum stability margin operating condition N of the engine with a stability margin less than a preset margin value. The unsteady analysis module is used to apply unsteady calculation boundary conditions to the CFD numerical simulation model of the multi-stage axial compressor, carry out unsteady flow field calculation of the multi-stage axial compressor under operating condition N, and determine the first stage of stall of the multi-stage axial compressor. The discrimination and processing module is used to open a self-circulation channel in the compressor casing corresponding to the rotor blade of the first stage when the stall of the multi-stage axial compressor is a rotor blade and the stall position is located at the blade tip, so as to form a self-circulation casing processing structure; the self-circulation casing processing structure consists of a nozzle, an extraction port and a self-circulation channel. The adjustment and optimization module is used to calculate the aerodynamic performance of a multi-stage axial compressor with a self-circulating casing treatment structure and perform engine stability analysis under N conditions using CFD methods, with the position and size parameters of the self-circulating casing treatment structure as design variables. The module obtains the dimensions of the self-circulating casing treatment structure that meet or exceed the preset margin value, and completes the design of the self-circulating casing treatment structure.
6. The design system for a self-circulating passive stabilization and expansion of a multi-stage axial compressor according to claim 5, characterized in that, In the discrimination processing module, if the first stage of stall of the multi-stage axial compressor is a stator blade, or the stall location is not at the tip of the rotor blade, the aerodynamic modeling data of the multi-stage axial compressor is adjusted until the stability margin of the engine under N condition is greater than or equal to the preset margin value.
7. The design system for a self-circulating passive stabilization and expansion of a multi-stage axial compressor according to claim 5, characterized in that, In the discrimination processing module, the blade tip is the region that is 20% of the blade height away from the blade tip of the rotor blade.
8. The design system for a self-circulating passive stabilization and expansion of a multi-stage axial compressor according to claim 5, characterized in that, In the adjustment and optimization module, the position of the self-circulating casing processing structure includes the nozzle position and the suction port position, and the dimensional parameters of the self-circulating casing processing structure include the nozzle aspect ratio, suction angle, and suction port aspect ratio.