Complete machine vibration reduction and impact resistance comprehensive design method for aeroderivative gas turbine

Abstract

The invention belongs to the field of aero-derivative gas turbine design, and particularly relates to a vibration reduction and impact resistance comprehensive design method for a whole aero-derivative gas turbine. The method comprises the steps that the design requirement of the aeroderivative gas turbine is determined; determining an initial structure scheme of the aeroderivative gas turbine according to design requirements; constructing a complete machine simulation model according to the initial structure scheme of the aeroderivative gas turbine; carrying out complete machine dynamics analysis and impact response analysis according to the complete machine simulation model to obtain a simulation result; judging whether the simulation result meets an evaluation standard or not; if the simulation result meets the evaluation standard, a verification test is carried out, a test result is obtained, and the step 6 is executed; if the simulation result does not meet the evaluation standard, carrying out problem identification and optimization design, and returning to correct the whole machine simulation model; judging whether a test result meets an evaluation standard or not; if the test result meets the evaluation standard, solidifying the aero-derivative gas turbine structure scheme; and if the test result does not meet the evaluation standard, carrying out problem identification and optimization design, and returning to correct the whole machine simulation model.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aero-derivative gas turbine design, and particularly relates to a comprehensive design method for vibration reduction and impact resistance of an aero-derivative gas turbine. BACKGROUND

[0002] In the design process of an aero-derivative gas turbine (referred to as an aero-derivative gas turbine), vibration reduction and impact resistance design are necessary strength design work at the whole machine level. At present, vibration reduction design and impact resistance design are independently carried out in the development process of the aero-derivative gas turbine.

[0003] Because the vibration reduction design and the impact resistance design are independently carried out in the development process of the aero-derivative gas turbine at present, there is a lack of cross consideration in the simulation analysis and iterative optimization process. The problems of repeated simulation modeling work, high iteration calculation frequency and conflict of scheme improvement direction frequently occur, and therefore the existing technical defects are as follows: low design efficiency, large redundant workload and poor comprehensive performance of vibration reduction and impact resistance of the scheme.

[0004] Therefore, there is an urgent need for a technical solution to overcome or alleviate at least one of the above-mentioned defects of the prior art. SUMMARY

[0005] The purpose of the present application is to provide a comprehensive design method for vibration reduction and impact resistance of an aero-derivative gas turbine to solve at least one problem existing in the prior art.

[0006] The technical solution of the present application is:

[0007] A comprehensive design method for vibration reduction and impact resistance of an aero-derivative gas turbine, comprising:

[0008] Step 1, determining the design requirements of the aero-derivative gas turbine;

[0009] Step 2, determining an initial structure scheme of the aero-derivative gas turbine according to the design requirements;

[0010] Step 3, constructing a whole machine simulation model suitable for whole machine dynamics analysis and impact response analysis according to the initial structure scheme of the aero-derivative gas turbine;

[0011] Step 4, carrying out whole machine dynamics analysis and impact response analysis according to the whole machine simulation model to obtain simulation results;

[0012] Step 5, judging whether the simulation results meet the evaluation criteria;

[0013] If the simulation results meet the evaluation criteria, a verification test is carried out to obtain test results, and step 6 is entered;

[0014] If the simulation results do not meet the evaluation criteria, problem identification and optimization design are carried out, and step 3 is returned to modify the whole machine simulation model;

[0015] Step six, judging whether the test result meets the evaluation standard;

[0016] If the test result meets the evaluation standard, the structure scheme of the solidified aero-derivative engine is determined.

[0017] If the test result does not meet the evaluation standard, problem identification and optimization design are carried out, and the whole machine simulation model is modified.

[0018] In at least one embodiment of the present application, in step one, the design requirements of the aero-derivative engine are determined, including:

[0019] The technical state, working speed, impact load, installation form and vibration index of the aero-derivative engine are determined.

[0020] In at least one embodiment of the present application, in step three, the whole machine simulation model includes:

[0021] The engine main machine, exhaust device, support system, box body and base vibration isolation system.

[0022] In at least one embodiment of the present application, in step four, the simulation result includes:

[0023] The whole machine dynamics analysis simulation result includes the critical speed of the main machine rotor-support system and the steady-state vibration response of the whole machine.

[0024] The impact response analysis simulation result includes the structural deformation under impact load, the rotor-stator gap and the stress of the main part examination site.

[0025] In at least one embodiment of the present application, in step five, judging whether the simulation result meets the evaluation standard includes:

[0026] The critical speed of the main machine rotor-support system meets the design specification requirements.

[0027] The steady-state vibration response of the whole machine meets the type development index requirements.

[0028] The structural deformation under impact load does not exceed the specified limit value.

[0029] The rotor-stator gap does not exceed the design gap value.

[0030] The stress of the main part examination site does not exceed the allowable stress value.

[0031] When all the above conditions are met, it is considered that the simulation result meets the evaluation standard.

[0032] In at least one embodiment of the present application, in step five, the verification test is carried out, and the test result is obtained, including:

[0033] Developing the whole machine test bench state vibration special test, obtaining the whole machine dynamics analysis test results, including the main rotor-support system critical speed, the whole machine steady-state vibration response;

[0034] Developing the impact test, obtaining the impact response analysis test results, including the structural deformation under impact load, the rotor-stator gap, and the stress of the main component examination part.

[0035] In at least one embodiment of the present application, in step six, determining whether the test results meet the evaluation criteria includes:

[0036] The main rotor-support system critical speed meets the design specification requirements;

[0037] The whole machine steady-state vibration response meets the type development index requirements;

[0038] The structural deformation under impact load does not exceed the specified limit value;

[0039] The rotor-stator gap does not exceed the design gap value;

[0040] The stress of the main component examination part does not exceed the allowable stress value;

[0041] When all the above meet, it is considered that the test results meet the evaluation criteria.

[0042] In at least one embodiment of the present application, in step five or step six, problem identification and optimization design are carried out, including:

[0043] If the whole machine dynamics analysis simulation results / whole machine dynamics analysis test results do not meet the evaluation criteria, a spring structure is set at a position away from the rotor-stator gap risk position under impact load in the whole machine simulation model; and,

[0044] If the impact response analysis simulation results / impact response analysis test results do not meet the evaluation criteria, a local strengthening structure is added in the whole machine simulation model.

[0045] The present application has at least the following beneficial technical effects:

[0046] The whole machine vibration reduction and impact resistance comprehensive design method of the turbofan engine of the present application establishes the comprehensive design technology of the vibration reduction design and the impact resistance design of the turbofan engine, which were originally carried out independently, by using a unified simulation model and collaborative optimization design, thereby improving the design efficiency, reducing redundant iterative calculation, and improving the comprehensive performance of vibration reduction and impact resistance. BRIEF DESCRIPTION OF DRAWINGS

[0047] Figure 1 is a flow chart of the whole machine vibration reduction and impact resistance comprehensive design method of the turbofan engine of an embodiment of the present application. DETAILED DESCRIPTION

[0048] For the purpose, technical solutions and advantages of the embodiments of the present application, the technical solutions in the embodiments of the present application will be described in more detail below. In the drawings, the same or similar reference numbers represent the same or similar elements or elements with the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, not all embodiments. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as limiting the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below with reference to the drawings.

[0049] The embodiments of the present application will be described in detail below with reference to the drawings. Figure 1 The present application will be described in further detail.

[0050] The present application provides a comprehensive design method for vibration reduction and impact resistance of an aero-derivative gas turbine, as shown in the following steps: Figure 1 The steps are as follows:

[0051] Step one, determine the design requirements of the aero-derivative gas turbine;

[0052] Step two, determine the initial structure scheme of the aero-derivative gas turbine according to the design requirements;

[0053] Step three, construct a whole machine simulation model suitable for whole machine dynamics analysis and impact response analysis according to the initial structure scheme of the aero-derivative gas turbine;

[0054] Step four, carry out whole machine dynamics analysis and impact response analysis according to the whole machine simulation model, and obtain simulation results;

[0055] Step five, judge whether the simulation results meet the evaluation criteria;

[0056] If the simulation results meet the evaluation criteria, carry out verification test to obtain test results, and enter step six;

[0057] If the simulation results do not meet the evaluation criteria, carry out problem identification and optimization design, and return to step three to modify the whole machine simulation model;

[0058] Step six, judge whether the test results meet the evaluation criteria;

[0059] If the test results meet the evaluation criteria, solidify the structure scheme of the aero-derivative gas turbine;

[0060] If the test results do not meet the evaluation criteria, carry out problem identification and optimization design, and return to step three to modify the whole machine simulation model.

[0061] The aero-derivative engine whole machine vibration reduction and impact resistance comprehensive design method of the application, first, in step one, design requirement analysis is carried out, and the design requirements of the aero-derivative engine, such as technical state, working speed, impact load, installation form, vibration index, etc. are determined.

[0062] Secondly, in step two, the aero-derivative engine initial structure scheme is formed according to the use requirements and performance indexes of the aero-derivative engine in the design requirements.

[0063] In step three, the whole machine simulation model suitable for whole machine dynamics analysis and impact response analysis is constructed according to the aero-derivative engine initial structure scheme. The whole machine simulation model includes: engine main machine, exhaust device, support system, box body, base vibration isolation system, etc., wherein the box body and the base vibration isolation system can be designed according to the needs.

[0064] In step four, the whole machine dynamics analysis and impact response analysis are carried out according to the whole machine simulation model, and the simulation results are obtained. The simulation results mainly include:

[0065] The whole machine dynamics analysis simulation results include the critical speed of the main machine rotor-support system, the steady-state vibration response of the whole machine;

[0066] The impact response analysis simulation results include the structure deformation under impact load, the rotor-stator gap, the stress of the main part of the examination site.

[0067] In this embodiment, according to the simulation results, the following analysis results can also be obtained: the relationship between the critical speed of the main machine rotor-support system and the working speed, the critical speed margin and the strain energy distribution, the steady-state vibration response unbalance sensitivity, the sensitive position of the structure deformation under impact load, the risk section of the rotor-stator gap, the stress condition of the main part of the examination site, the impact dangerous frequency range, etc.

[0068] Among them, in the simulation calculation, the whole machine dynamics analysis parameters and the impact response analysis parameters are input into the whole machine simulation model at the same time, the output whole machine dynamics analysis simulation results consider the influence of impact response, the impact response analysis simulation results consider the influence of vibration response, and it is recommended to adopt the vibration response caused by the maximum allowable residual unbalance excitation of the rotor.

[0069] In step five, the general evaluation standard for the above simulation results is as follows:

[0070] The critical speed of the main machine rotor-support system meets the design specification requirements;

[0071] The steady-state vibration response of the whole machine meets the type development index requirements;

[0072] The structure deformation under impact load does not exceed the specified limit value;

[0073] The rotor-stator gap does not exceed the design gap value;

[0074] The stress at the test points of major components shall not exceed the allowable stress value;

[0075] If all of the above conditions are met, the simulation results are considered to meet the evaluation criteria.

[0076] If all the above evaluation criteria are met, then a verification experiment will be conducted to obtain the experimental results.

[0077] If there are evaluation criteria that cannot be met, it is necessary to carry out problem identification and optimization design work, and return to step three of establishing the whole machine simulation model to carry out model correction work.

[0078] Verification tests are conducted to determine the design compliance and to correct the overall simulation model.

[0079] First, conduct a special vibration test on the test bench of the whole machine to obtain the test results of the whole machine dynamic analysis, including the critical speed of the main rotor-support system and the steady-state vibration response of the whole machine;

[0080] Conduct impact tests to obtain impact response analysis results, including structural deformation under impact load, rotor-stator clearance, and stress at key component test sites.

[0081] Prioritize conducting special vibration tests on the whole machine test bench. Based on the results of the critical speed test and the vibration response of the whole machine under all working conditions, verify that the dynamic design (i.e., critical speed and steady-state response) meets the design requirements.

[0082] Impact tests should be conducted on a professional impact testing platform. Test sensors should be arranged according to the calculation results and the actual conditions of the testing platform. Generally, no vibration limit requirements are set for the whole machine during the impact test, but attention should be paid to the difference in vibration performance before and after the impact test in order to improve the vibration limit standards for the whole machine.

[0083] In step six, the general evaluation criteria for the test results are as follows:

[0084] The critical speed of the main rotor-support system meets the design specifications.

[0085] The overall steady-state vibration response of the machine meets the requirements of the model development specifications.

[0086] The structural deformation under impact load shall not exceed the specified limit.

[0087] The rotor-stator clearance should not exceed the design clearance value;

[0088] The stress at the test points of major components shall not exceed the allowable stress value;

[0089] If all of the above conditions are met, the test results are considered to meet the evaluation criteria.

[0090] If all the above evaluation criteria are met, the aero-to-gas turbine structural design will be solidified.

[0091] If there are evaluation criteria that cannot be met, it is necessary to carry out problem identification and optimization design work, and return to step three of establishing the whole machine simulation model to carry out model correction work.

[0092] In step five or six, the problem identification and optimization design work is carried out when the simulation results do not meet the design specifications or the test results do not meet the index requirements, and it is iterated until the requirements are met.

[0093] If the simulation results of the whole-machine dynamics analysis / the test results of the whole-machine dynamics analysis do not meet the evaluation criteria, then a spring support structure shall be set in the whole-machine simulation model at a location far from the risk position of the rotor-stator gap under impact load; and,

[0094] If the simulation results of the impact response analysis / the test results of the impact response analysis do not meet the evaluation criteria, a local reinforcement structure will be added to the whole machine simulation model.

[0095] In the preferred embodiment of this application, if the vibration reduction design does not meet the requirements, optimization design work should be carried out under the premise of fully considering the impact resistance performance; when setting the spring support structure, it should be as far away as possible from the risk position of rotor-stator clearance under impact load, and the spring support limiting clearance should be strictly controlled; when performing local dynamic optimization design, it should be ensured that the stress risk position under impact load does not exceed the allowable stress value. If the impact resistance design does not meet the requirements, the optimization design process should also fully consider the dynamic characteristics of the gas turbine as a whole; when performing local reinforcement, it should be ensured that the margin of the affected critical speed relative to the commonly used operating speed still meets the requirements, the rotor strain energy within the operating speed range does not exceed the standard requirements, and the overall vibration response does not exceed the limit requirements. If neither of the requirements is met, a systematic optimization design should be carried out, and in-depth optimization design should be performed on the aero-derivative gas turbine damping system (including the main engine internal damper and the base vibration isolator, etc.).

[0096] The integrated design method for vibration reduction and impact resistance of the aero-derivative gas turbine in this application, based on the final optimized whole-machine simulation model, solidifies the aero-derivative gas turbine structural scheme that finally meets the design requirements for vibration reduction and impact resistance into the overall design of the aero-derivative gas turbine.

[0097] The integrated design method for vibration reduction and shock resistance of the aero-derivative gas turbine proposed in this application adopts the same simulation analysis model for both vibration reduction and shock resistance design, which effectively improves design efficiency; the vibration reduction and shock resistance design are carried out in a coordinated manner, and the design is systematically optimized to reduce redundant iterative calculations; the same set of simulation analysis model that has been experimentally corrected is used, and the calculation results mutually verify the high accuracy of vibration reduction and shock resistance analysis. The collaborative design process takes into account the mutual influence of the designs, which can effectively improve the overall performance of vibration reduction and shock resistance.

[0098] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A comprehensive design method for vibration reduction and impact resistance of an aero-derivative gas turbine, characterized in that, include: Step 1: Determine the design requirements for aero-derivative gas turbines; Step 2: Determine the initial structural scheme of the aero-to-gas turbine based on design requirements; Step 3: Based on the initial structural design of the aero-derivative gas turbine, construct a whole-engine simulation model suitable for overall dynamics analysis and impact response analysis; Step 4: Conduct overall dynamics analysis and impact response analysis based on the overall machine simulation model, and obtain simulation results; Step 5: Determine whether the simulation results meet the evaluation criteria; If the simulation results meet the evaluation criteria, then conduct a verification experiment, obtain the experimental results, and proceed to step six; If the simulation results do not meet the evaluation criteria, then carry out problem identification and optimization design, return to step three, and correct the whole machine simulation model; Step Six: Determine whether the test results meet the evaluation criteria; If the test results meet the evaluation criteria, the aero-to-gas turbine structural design will be solidified. If the test results do not meet the evaluation criteria, then problem identification and optimization design will be carried out, and the process will return to step three to revise the whole machine simulation model.

2. The integrated design method for vibration reduction and impact resistance of the entire aero-derivative gas turbine as described in claim 1, characterized in that, Step one involves determining the design requirements for the aero-derivative gas turbine, including: Determine the technical condition, operating speed, impact load, installation method, and vibration index of the aero-derivative gas turbine.

3. The integrated design method for vibration reduction and impact resistance of the entire aero-derivative gas turbine as described in claim 2, characterized in that, In step three, the whole machine simulation model includes: Gas turbine main unit, exhaust device, support system, housing, and base vibration isolation system.

4. The integrated design method for vibration reduction and impact resistance of the entire aero-derivative gas turbine as described in claim 3, characterized in that, In step four, the simulation results include: The simulation results of the whole machine dynamics analysis include the critical speed of the main rotor-support system and the steady-state vibration response of the whole machine; The impact response analysis and simulation results include structural deformation under impact load, rotor-stator clearance, and stress at key component test locations.

5. The integrated design method for vibration reduction and impact resistance of the entire aero-derivative gas turbine as described in claim 4, characterized in that, Step five involves determining whether the simulation results meet the evaluation criteria, including: The critical speed of the main rotor-support system meets the design specifications. The overall steady-state vibration response of the machine meets the requirements of the model development specifications. The structural deformation under impact load shall not exceed the specified limit. The rotor-stator clearance should not exceed the design clearance value; The stress at the test points of major components shall not exceed the allowable stress value; If all of the above conditions are met, the simulation results are considered to meet the evaluation criteria.

6. The integrated design method for vibration reduction and impact resistance of the entire aero-derivative gas turbine as described in claim 5, characterized in that, Step five involves conducting verification experiments and obtaining the results, including: Conduct special vibration tests on the test bench of the whole machine to obtain the test results of the whole machine dynamic analysis, including the critical speed of the main rotor-support system and the steady-state vibration response of the whole machine; Conduct impact tests to obtain impact response analysis results, including structural deformation under impact load, rotor-stator clearance, and stress at key component test sites.

7. The integrated design method for vibration reduction and impact resistance of the entire aero-derivative gas turbine as described in claim 6, characterized in that, Step six involves determining whether the test results meet the evaluation criteria, including: The critical speed of the main rotor-support system meets the design specifications. The overall steady-state vibration response of the machine meets the requirements of the model development specifications. The structural deformation under impact load shall not exceed the specified limit. The rotor-stator clearance should not exceed the design clearance value; The stress at the test points of major components shall not exceed the allowable stress value; If all of the above conditions are met, the test results are considered to meet the evaluation criteria.

8. The integrated design method for vibration reduction and impact resistance of the entire aero-derivative gas turbine as described in claim 7, characterized in that, In step five or six, problem identification and optimization design are carried out, including: If the simulation results of the whole-machine dynamics analysis / the test results of the whole-machine dynamics analysis do not meet the evaluation criteria, then a spring support structure shall be set in the whole-machine simulation model at a location far from the risk position of the rotor-stator gap under impact load; and, If the simulation results of the impact response analysis / the test results of the impact response analysis do not meet the evaluation criteria, a local reinforcement structure will be added to the whole machine simulation model.

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