Test Method for Blade Containment and Rotor Unbalance Design of Aeroengine

Abstract

This application belongs to the field of aero-engine overall blade containment and rotor imbalance design tests, and specifically relates to a method for aero-engine overall blade containment and rotor imbalance design tests. Based on the structural integrity requirements of the blade containment and rotor imbalance tests of the aero-engine overall, through decoupled design, simulation, and test verification, after ensuring that the designs of each structure meet the requirements, overall machine integrated simulation is carried out to further analyze the structural integrity of the overall machine under the coupling effect, ensuring that the aero-engine meets the requirements in terms of structural design. Finally, the blade containment and rotor imbalance tests of the overall machine are carried out in the design. The overall method uses a progressive step-by-step verification method, which can greatly reduce the high risk and ensure the success rate of a single test.

Description

Technical Field

[0001] This application belongs to the field of aero-engine whole-machine blade containment and rotor imbalance design tests, and specifically relates to a method for aero-engine whole-machine blade containment and rotor imbalance design tests. Background Art

[0002] The blade containment and rotor imbalance tests assess the containment capacity of the casing and the ability of the load-bearing structure to withstand large rotor imbalance loads under the action of the blade loss load of the aero-engine.

[0003] To obtain an airworthiness certificate and complete the blade containment and rotor imbalance tests based on the aero-engine whole machine, the main requirements for the structural integrity of the aero-engine mainly include the casing containment capacity, the load-bearing capacity of the load-bearing system, the torsional resistance capacity of the low-pressure shaft, and the fire and heat resistance capacity of the accessories and pipelines.

[0004] Currently, for the design of aero-engines, most are based on component tests. For the blade containment and rotor imbalance tests of the aero-engine whole machine, there is a lack of a systematic, comprehensive, and scientific distributed step-by-step verification method, with high risk and it is difficult to ensure the success rate of a single test.

[0005] In view of the existence of the above technical defects, this application is proposed.

[0006] It should be noted that the disclosure of the above background art content is only for assisting in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. Without clear evidence indicating that the above content was publicly available on the filing date of this application, the above background art should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0007] The purpose of this application is to provide a method for aero-engine whole-machine blade containment and rotor imbalance design tests to overcome or mitigate at least one aspect of the known technical defects.

[0008] The technical solution of this application is as follows:

[0009] A method for aero-engine whole-machine blade containment and rotor imbalance design tests includes:

[0010] Determine the test verification parameters;

[0011] Decompose the test verification parameters to obtain the design load requirements for each structure of the aero-engine;

[0012] Conduct casing containment capacity design and perform casing containment capacity simulation;

[0013] Design the load-bearing capacity of the load-bearing system, design the main load-bearing frame, conduct static strength simulation of the main load-bearing frame, and design the installation system and conduct strength simulation of the installation system;

[0014] Design the anti-torsion ability of the low-pressure shafting and conduct anti-torsion ability simulation of the low-pressure shafting;

[0015] Design the fire and heat resistance ability of the components and pipelines and conduct fire and heat resistance ability simulation of the components and pipelines;

[0016] After the simulation results of the casing containment ability, the static strength of the main load-bearing frame, the strength of the installation system, and the fire and heat resistance ability of the components and pipelines meet the design requirements:

[0017] Conduct component test verification of the casing containment ability;

[0018] Conduct test verification of the load-bearing capacity of the load-bearing system and conduct static test verification on the connection structures of the main load-bearing frame and the installation system;

[0019] Conduct test verification of the anti-torsion ability of the low-pressure shafting;

[0020] Conduct test verification of the fire and heat resistance ability of the components and pipelines;

[0021] After the component test verification of the casing containment ability, the static test verification of the connection structures of the load-bearing frame and the installation system, the test verification of the anti-torsion ability of the low-pressure shafting, and the test verification of the fire and heat resistance ability of the components and pipelines meet the design requirements:

[0022] Based on the corresponding casing, load-bearing system, and low-pressure shaft, design and conduct simulation of the blade containment and rotor imbalance of the whole engine. If the simulation results meet the design requirements, then:

[0023] Based on the corresponding casing, load-bearing system, low-pressure shaft, components and pipelines, adopt the test verification parameters and design and conduct the blade containment and rotor imbalance test of the whole engine.

[0024] According to at least one embodiment of the present application, in the above-mentioned design and test method for the blade containment and rotor imbalance of the aero-engine whole machine, determine the test verification parameters, specifically:

[0025] According to the requirements of airworthiness regulations and combined with the actual characteristics of the aero-engine, determine the test verification parameters, including the blade fracture position, blade fracture speed, test shutdown procedure, and test passing standard.

[0026] According to at least one embodiment of the present application, in the above-mentioned design and test method for the blade containment and rotor imbalance of the aero-engine whole machine, conduct the design of the casing containment ability and conduct the simulation of the casing containment ability, specifically:

[0027] Design the structural forms and material selections for the casings corresponding to the fan, high-pressure compressor, high-pressure turbine, and low-pressure turbine rotor blades;

[0028] Simulate the containment of the casing under the impact load of blade fracture to evaluate the containment capacity of the casing;

[0029] Conduct the design of the load-bearing capacity of the load-bearing system, design the main load-bearing frame, conduct the static strength simulation of the main load-bearing frame, and design the installation system and conduct the strength simulation of the installation system. Specifically:

[0030] Design the structural forms of the bearings, bearing housings, main load-bearing frames, installation systems, and the connection structures of the above-mentioned structures that transmit the lost load;

[0031] Simulate the static strength of the load-bearing system under the large unbalanced load after blade loss, analyze the strength reserve under the impact load, and evaluate the load-bearing capacity of the main load-bearing frame on the force transmission route against the impact of the blade loss load;

[0032] Conduct the design of the anti-torsion ability of the low-pressure shafting and conduct the simulation of the anti-torsion ability of the low-pressure shafting. Specifically:

[0033] Design the structural forms of the fan shaft, low-pressure turbine shaft, and coupling that transmit torque loads;

[0034] Simulate the anti-torsion ability of the low-pressure shafting under the torsional load of the collision and rubbing between the rotor blade and the casing, and evaluate the anti-torsion ability of the low-pressure rotor system;

[0035] Conduct the design of the fire and heat resistance of the accessories and pipelines and conduct the simulation of the fire and heat resistance of the accessories and pipelines. Specifically:

[0036] Design the structural forms, sealing forms, and material selections of the accessories and pipelines;

[0037] Simulate the fire and heat resistance of the accessories and pipelines and evaluate the fire and heat resistance of the accessories and pipelines.

[0038] According to at least one embodiment of the present application, in the above-mentioned aero-engine whole-machine blade containment and rotor imbalance design test method, when conducting the component test verification of the casing containment capacity:

[0039] Ensure that the technical states of the test components and the key influencing components related to the casing containment capacity verification meet the requirements of the casing containment capacity verification, including rotor blades and casings;

[0040] Verify and debug the blade fracture mode to ensure that the blade fracture speed and fracture position meet the test parameter requirements, and the test load meets the verification requirements;

[0041] Conduct the load-bearing capacity test verification of the load-bearing system. When conducting the static test verification on the main load-bearing frame and the connection structure of the installation system:

[0042] Ensure that the technical states of the test components related to the key components affecting the load-bearing capacity verification of the load-bearing system meet the verification requirements, including the main load-bearing frame, bearing seats, installation system and related connection structures, and force transmission casings;

[0043] Calculate the fly-off load applied to the test to ensure that the applied static load capacity represents the fly-off load of the blade and meets the verification requirements;

[0044] When conducting the anti-torsion ability test verification of the low-pressure shafting:

[0045] Ensure that the technical states of the test pieces related to the ability verification of the low-pressure rotor system meet the verification requirements, including the fan shaft, low-pressure turbine shaft and related connection structures;

[0046] Calculate the torque load applied to the test to ensure that the applied load capacity represents the jamming load between the blade and the casing after the blade fly-off and meets the verification requirements;

[0047] When conducting the fire and heat resistance ability test verification of the accessories and pipelines:

[0048] Select test components including pipelines and accessories with different specifications, different sealing forms, different materials, and different flowing media representing all pipelines to verify the fire and heat resistance abilities of key pipelines and accessories.

[0049] According to at least one embodiment of the present application, in the above-mentioned aero-engine whole-machine blade containment and rotor imbalance design test method, when designing the whole-machine blade containment and rotor imbalance simulation with the corresponding casing, load-bearing system, and low-pressure shaft:

[0050] Apply the whole-machine model to conduct blade containment and anti-rotor imbalance simulation, and carry out simulation analysis on the containment ability of the fan casing after the blade fly-off under the whole-machine condition;

[0051] Apply the whole-machine model to conduct strength assessment of the load-bearing system, analyze the fly-off load of the blade and its transmission law, and evaluate the low-pressure rotor shafting, each support bearing seat, intermediate casing, turbine rear casing, installation system, main connection structures on the force transmission route, casing connection structures, and external accessory connection structures;

[0052] Apply the whole-machine model to analyze the dynamic behavior of the whole machine after the blade fly-off;

[0053] Analyze the energy level and trajectory of the blade fragments after the fan blade fly-off. Description of the Drawings

[0054] Figure 1It is a flowchart of the test method for the blade containment and rotor imbalance design of an aero-engine provided by an embodiment of the present application. Detailed implementation manners

[0055] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further described clearly and completely in conjunction with the accompanying drawings. It can be understood that the specific embodiments described herein are only partial embodiments of the present application, which are only used to explain the present application rather than limit the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0056] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should be the ordinary meanings understood by those of ordinary skill in the art to which the present application belongs. The words indicating directions such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of the present application are only used to represent relative directions or position relationships, rather than implying that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative position relationship may also change accordingly. Therefore, it should not be understood as a limitation to the present application. The terms "first", "second", "third" and similar terms used in the description of the present application are only for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The similar words such as "one", "a" or "the" used in the description of the present application should not be understood as an absolute limitation on the quantity, but should be understood as having at least one. The similar words such as "including" or "comprising" used in the description of the present application are intended to mean that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0057] In addition, it should also be noted that unless otherwise clearly specified and limited, the similar words such as "installed", "connected" and "coupled" used in the description of the present application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and can also be the communication inside two elements. Those skilled in the art can understand its specific meaning in the present application according to the specific situation.

[0058] The following will Figure 1 make a further detailed description of the present application.

[0059] An experimental method for the blade containment and rotor imbalance design of an aero-engine, comprising:

[0060] S1. Determine the test verification parameters.

[0061] According to the requirements of airworthiness regulations and combined with the actual characteristics of the aero-engine, determine the test verification parameters, including the blade fracture position, blade fracture speed, test shutdown procedure, and test pass criteria.

[0062] S2. Decompose the test verification parameters into loads to obtain the design load requirements for each structure of the aero-engine.

[0063] S31. Design and perform strength simulations on the casing, load-bearing system, and low-pressure shafting, and complete the material selection design for the accessories, pipelines, etc.

[0064] S31. Conduct the design of the casing containment capacity and perform the simulation of the casing containment capacity.

[0065] Design the structural form and material selection for the casings corresponding to the fan, high-pressure compressor, high-pressure turbine, and low-pressure turbine rotor blades;

[0066] Simulate the containment capacity of the casing under the impact load of blade fracture to evaluate the casing containment capacity.

[0067] S32. Conduct the design of the load-bearing capacity of the load-bearing system, design the main load-bearing frame, perform the static strength simulation of the main load-bearing frame, and design the installation system and perform the strength simulation of the installation system.

[0068] Design the structural form for the bearings, bearing housings, main load-bearing frames, installation systems, and the connection structures of the above structures that transmit the lost load;

[0069] Simulate the static strength of the load-bearing system under the large unbalanced load after blade loss, analyze the strength reserve under the impact load, and evaluate the load-bearing capacity of the main load-bearing frame on the force transmission route against the impact load of blade loss.

[0070] S33. Conduct the design of the anti-torsion ability of the low-pressure shafting and perform the simulation of the anti-torsion ability of the low-pressure shafting.

[0071] Design the structural form for the fan shaft, low-pressure turbine shaft, and coupling that transmit torque loads;

[0072] Simulate the anti-torsion ability of the low-pressure shafting under the torsional load of the rotor blade rubbing against the casing to evaluate the anti-torsion ability of the low-pressure rotor system.

[0073] S34. Conduct the design of the fire and heat resistance of the accessories, pipelines, etc., and perform the simulation of the fire and heat resistance of the accessories, pipelines, etc., which can be limited to key accessories and pipelines.

[0074] Design the structural form, sealing form, and material selection of the mating accessories and pipelines;

[0075] Simulate the fire and heat resistance ability of the mating accessories and pipelines, and evaluate their fire and heat resistance ability.

[0076] If any of the simulation results of the casing containment ability simulation, main load-bearing frame static strength simulation, installation system strength simulation, and fire and heat resistance ability simulation of the mating accessories and pipelines fails to meet the design requirements, then return for re-optimized design and simulation.

[0077] S4. Conduct experimental verification on the casing, load-bearing system, low-pressure shaft, mating accessories and pipelines.

[0078] S41. Conduct experimental verification on the casing containment ability components.

[0079] Ensure that the technical states of the test components related to the key influencing components of the casing containment ability verification meet the requirements of the casing containment ability verification, including rotor blades and casings;

[0080] Verify and debug the blade fracture mode to ensure that the blade fracture speed and fracture position meet the test parameter requirements, and the test load meets the verification requirements.

[0081] S42. Conduct experimental verification on the load-bearing capacity of the load-bearing system, and conduct static experimental verification on the connection structures of the main load-bearing frame and the installation system.

[0082] Ensure that the technical states of the test components related to the key influencing components of the load-bearing capacity verification of the load-bearing system meet the verification requirements, including the main load-bearing frame, bearing seats, installation systems and related connection structures, and force transmission casings;

[0083] Calculate the lost load applied in the test to ensure that the applied static load capacity represents the lost load of the blade and meets the verification requirements.

[0084] S43. Conduct experimental verification on the anti-torsion ability of the low-pressure shafting.

[0085] Ensure that the technical states of the test pieces related to the key influencing components of the low-pressure rotor system ability verification meet the verification requirements, including the fan shaft, low-pressure turbine shaft and related connection structures;

[0086] Calculate the torque load applied in the test to ensure that the applied load capacity represents the jamming load between the blade and the casing after the blade is lost and meets the verification requirements.

[0087] S44. Conduct experimental verification on the fire and heat resistance ability of the mating accessories and pipelines.

[0088] Select test components to represent pipelines and their accessories with different specifications, different sealing forms, different materials, and different flowing media, and verify the fire resistance of key pipelines and their accessories.

[0089] If any verification result in the tests for validating the casing containment capacity components, the static tests for validating the connection structures of the load-bearing frame and the installation system, the tests for validating the anti-torsion ability of the low-pressure shafting, and the fire resistance tests for accessories and pipelines does not meet the design requirements, then, in combination with the damaged structure, measurement data such as stress, strain, vibration, and camera data, conduct cause analysis to determine the specific improved design plan, and then return to re-perform the optimized design and simulation.

[0090] S 5. Use the corresponding casing, load-bearing system, and low-pressure shaft to design and conduct the simulation of the blade containment and rotor imbalance of the whole engine.

[0091] S51. Apply the whole-engine model to conduct the simulation of blade containment and anti-rotor imbalance, and carry out the simulation analysis of the fan casing containment capacity after a blade is lost under the whole-engine condition.

[0092] S52. Apply the whole-engine model to conduct the strength assessment of the load-bearing system, analyze the load and transmission law of the lost blade, and evaluate the low-pressure rotor shafting, each support bearing housing, intermediate casing, turbine rear casing, installation system, main connection structures on the force transmission route, the connection structure between the casings, and the connection structure of external accessories.

[0093] S53. Apply the whole-engine model to analyze the dynamic behavior of the whole engine after a blade is lost.

[0094] S54. Analyze the energy level and trajectory of the blade fragments after a fan blade is lost.

[0095] If the simulation of the blade containment and rotor imbalance of the whole engine cannot meet the design requirements, then re-perform the corresponding structural optimization design and simulation.

[0096] Step Six. Use the corresponding casing, load-bearing system, low-pressure shaft, accessories and pipelines, and adopt the test verification parameters to design and conduct the blade containment and rotor imbalance tests of the whole engine.

[0097] For the method of designing and testing the blade containment and rotor imbalance of the aero-engine whole engine disclosed in the above embodiments, those skilled in the art can understand that, based on the requirements for structural integrity in the blade containment and rotor imbalance tests of the aero-engine whole engine, through decoupled design, simulation, and test verification, after ensuring that the designs of each structure meet the requirements, conduct the integrated simulation of the whole engine to further analyze the structural integrity of the whole engine under the coupling effect, ensure that the aero-engine meets the requirements in terms of structural design, and finally design and conduct the blade containment and rotor imbalance tests of the whole engine. The overall method of progressive step-by-step verification can greatly reduce the high risk and ensure the success rate of a single test.

[0098] The various embodiments in the specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. For the same or similar parts among the various embodiments, reference can be made to each other.

[0099] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of the present application.

Claims

1. A test method for the blade containment and rotor imbalance design of an entire aeroengine, characterized in that, Including: Determine the test verification parameters; Decompose the test verification parameters for the load to obtain the design load requirements for each structure of the aero-engine; Conduct the design of the casing containment capacity and perform the simulation of the casing containment capacity; Conduct the design of the load-bearing capacity of the load-bearing system, design the main load-bearing frame, perform the static strength simulation of the main load-bearing frame, and design the installation system and perform the strength simulation of the installation system; Conduct the design of the anti-torsion ability of the low-pressure shafting and perform the simulation of the anti-torsion ability of the low-pressure shafting; Conduct the design of the fire and heat resistance ability of the accessories and pipelines and perform the simulation of the fire and heat resistance ability of the accessories and pipelines; After the simulation results of the casing containment capacity, the static strength of the main load-bearing frame, the strength of the installation system, and the fire and heat resistance ability of the accessories and pipelines meet the design requirements: Conduct the component test verification of the casing containment capacity; Conduct the test verification of the load-bearing capacity of the load-bearing system and conduct the static test verification on the connection structures of the main load-bearing frame and the installation system; Conduct the test verification of the anti-torsion ability of the low-pressure shafting; Conduct the test verification of the fire and heat resistance ability of the accessories and pipelines; After the component test verification of the casing containment capacity, the static test verification on the connection structures of the load-bearing frame and the installation system, the test verification of the anti-torsion ability of the low-pressure shafting, and the test verification of the fire and heat resistance ability of the accessories and pipelines meet the design requirements: Based on the corresponding casing, load-bearing system, and low-pressure shaft, design and conduct the simulation of the blade containment and rotor imbalance of the whole engine. If the simulation results meet the design requirements, then: Based on the corresponding casing, load-bearing system, low-pressure shaft, accessories and pipelines, adopt the test verification parameters and design and conduct the test of the blade containment and rotor imbalance of the whole engine.

2. The test method for the blade containment and rotor imbalance design of an entire aeroengine according to claim 1, characterized in that, Determine the test verification parameters, specifically: According to the requirements of the airworthiness regulations and combined with the actual characteristics of the aero-engine, determine the test verification parameters, including the blade fracture position, blade fracture speed, test shutdown procedure, and test passing criteria.

3. The test method for the blade containment and rotor imbalance design of an entire aeroengine according to claim 1, characterized in that, Conduct the design of the casing containment capacity and perform the simulation of the casing containment capacity, specifically: Design the structural form and material selection for the casings corresponding to the fan, high-pressure compressor, high-pressure turbine, and low-pressure turbine rotor blades; Simulate the containment of the casing under the impact load of blade fracture and evaluate the casing containment capacity; Conduct the design of the load-bearing capacity of the load-bearing system, design the main load-bearing frame, perform the static strength simulation of the main load-bearing frame, and design the installation system and perform the strength simulation of the installation system, specifically: Design the structural form for the bearings, bearing seats, main load-bearing frame, installation system, and the connection structures of the above structures that transfer the lost load; Simulate the static strength of the load-bearing system under the large unbalanced load after blade loss, analyze the strength reserve under the impact load, and evaluate the load-bearing capacity of the main load-bearing frame on the load transfer path against the impact of blade loss load; Conduct the design of the anti-torsion ability of the low-pressure shafting and perform the simulation of the anti-torsion ability of the low-pressure shafting, specifically: Design the structural form for the fan shaft, low-pressure turbine shaft, and coupling that transfer the torque load; Simulate the anti-torsion ability of the low-pressure shafting under the torsional load of the rotor blade rubbing against the casing and evaluate the anti-torsion ability of the low-pressure rotor system; Conduct the design of the fire and heat resistance ability of the accessories and pipelines and perform the simulation of the fire and heat resistance ability of the accessories and pipelines, specifically: Design the structural form, sealing form, and material selection of the accessory and pipeline. Simulate the fire and heat resistance of the accessory and pipeline, and evaluate their fire and heat resistance capabilities.

4. The test method for the blade containment and rotor imbalance design of an entire aeroengine according to claim 1, characterized in that, When conducting the component test verification of the casing containment ability: Ensure that the technical states of the test components and the key influencing components related to the casing containment ability verification meet the requirements of the casing containment ability verification, including rotor blades and the casing. Verify and debug the blade fracture mode to ensure that the blade fracture speed and fracture position meet the test parameter requirements, and the test load meets the verification requirements. When conducting the test verification of the load-bearing capacity of the load-bearing system and performing the static test verification on the connection structures of the main load-bearing frame and the installation system: Ensure that the technical states of the test components and the key influencing components related to the load-bearing capacity verification of the load-bearing system meet the verification requirements, including the main load-bearing frame, bearing seats, installation system and related connection structures, and the force transmission casing. Calculate the thrown-off load applied in the test to ensure that the applied static load capacity represents the thrown-off load of the blade and meets the verification requirements. When conducting the test verification of the anti-torsion ability of the low-pressure shafting: Ensure that the technical states of the test pieces and the key influencing components related to the low-pressure rotor system ability verification meet the verification requirements, including the fan shaft, low-pressure turbine shaft and related connection structures. Calculate the torque load applied in the test to ensure that the applied load capacity represents the jamming load between the blade and the casing after the blade is thrown off and meets the verification requirements. When conducting the test verification of the fire and heat resistance of the accessory and pipeline: Select test components including pipelines and accessories with different specifications, different sealing forms, different material selections, and different flowing media representing all pipelines to verify the fire and heat resistance of key pipelines and accessories.

5. The test method for the blade containment and rotor imbalance design of an aero-engine as claimed in claim 1, wherein, When designing the simulation of the blade containment and rotor imbalance of the whole machine with the corresponding casing, load-bearing system, and low-pressure shaft: Apply the whole-machine model to conduct the simulation of blade containment and anti-rotor imbalance, and carry out the simulation analysis of the fan casing containment ability after the blade is thrown off under the whole-machine conditions. Apply the whole-machine model to evaluate the strength of the load-bearing system, analyze the thrown-off load of the blade and its transmission law, and evaluate the low-pressure rotor shafting, each support bearing seat, intermediate casing, rear turbine casing, installation system, main connection structures on the force transmission route, casing connection structures, and external accessory connection structures. Apply the whole-machine model to analyze the dynamic behavior of the whole machine after the blade is thrown off. Analyze the energy level and trajectory of the blade fragments after the fan blade is thrown off.

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