CN116006327B - A strength assessment method for double-layer turbine blades with reverse rotation function - Google Patents
A strength assessment method for double-layer turbine blades with reverse rotation function Download PDFInfo
- Publication number
- CN116006327B CN116006327B CN202211534136.1A CN202211534136A CN116006327B CN 116006327 B CN116006327 B CN 116006327B CN 202211534136 A CN202211534136 A CN 202211534136A CN 116006327 B CN116006327 B CN 116006327B
- Authority
- CN
- China
- Prior art keywords
- blade
- double
- layer
- gas
- calculation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention aims to provide a double-layer turbine blade strength assessment method with a reverse rotation function, which comprises the following steps of establishing a three-dimensional coupling model of a double-layer turbine blade and a wheel disc, determining normal rotation rated working condition operation parameters, reverse rotation rated working condition operation parameters and gas switching transition working condition operation parameters of the double-layer turbine blade, calculating the normal rotation working condition, calculating the reverse rotation working condition, calculating the gas switching transition working condition, and respectively carrying out strength assessment on all positions of the double-layer turbine blade under three working conditions. The method considers that the double-layer turbine blade has special double-layer structure characteristics and running environment characteristics, and considers the influence of the friction heat generation of the blade and the air on the temperature field of the blade and the influence of the gas switching transition working condition on the double-layer turbine blade in the strength calculation. And the intensity calculation of the double-layer turbine blade is more comprehensive and accurate.
Description
Technical Field
The invention relates to a strength assessment method, in particular to a turbine strength assessment method of a gas turbine.
Background
The reversing gas turbine is favored by various countries because of the characteristics of high reversing power density, quick starting and the like, and becomes one of the main power devices of the ship. The reversing gas turbine adopts the design concept of double gas channels and double turbine blades, and the outer channel is a reversing channel. The inner channel is a forward channel, the distribution of a gas flow route is realized through a gas switching mechanism at the front end, when gas only flows through the lower layer turbine blades, the turbine rotor rotates positively, and when gas only flows through the upper layer turbine blades, the turbine rotor rotates reversely. The double-layer turbine blade is used as a core component in the reversing gas turbine, and the running reliability of the double-layer turbine blade is directly related to the safety of the whole gas turbine, so that in the design process, the double-layer turbine blade is required to be subjected to strength calculation, and the weak strength position is eliminated, so that the double-layer turbine blade obtains the strength reserve as large as possible, and the long-term use requirement is met.
When the gas only flows through the lower layer turbine blades, the turbine rotor rotates positively, no gas flows through the upper layer turbine blades at the position of the upper layer turbine blades, the upper layer turbine blades rotate against the design direction, air is continuously stirred, heat is generated by friction with the air, the temperature field distribution of the double-layer turbine blades is influenced, and the strength of the double-layer turbine blades is greatly influenced by the change of the temperature field. When the combustion gases flow only through the upper turbine blades, the turbine rotor rotates in the opposite direction, and similar conditions exist for the blades. Therefore, the influence of blade agitation air frictional heating on blade strength should also be considered in the double-layer turbine blade strength assessment. In addition, under the transitional condition of gas switching, the gas flows through the upper turbine blade and the lower turbine blade at the same time, and at a certain balance position, the torque generated by the gas on the upper turbine blade and the lower turbine blade is equal and opposite, and at the position, the connection position of the upper turbine blade and the lower turbine blade is required to generate a weak point in strength. Therefore, in the double-layer turbine blade strength assessment, besides the forward rotation working condition and the reverse rotation working condition, the double-layer turbine blade strength characteristic under the transition working condition is considered. Because the double-layer turbine blade has special double-layer structural characteristics and running environment characteristics, the strength characteristics of the double-layer turbine blade cannot be comprehensively evaluated by the traditional single-layer turbine blade strength calculation method.
Disclosure of Invention
The invention aims to provide the double-layer turbine blade strength checking method with the reverse rotation function, which can solve the problem of double-layer turbine blade strength checking and obtain the double-layer turbine blade structure with high reliability and simple structure.
The purpose of the invention is realized in the following way:
The invention relates to a double-layer turbine blade strength checking method with a reverse rotation function, which is characterized by comprising the following steps of:
(1) Establishing a three-dimensional coupling model of the double-layer turbine blade and the wheel disc in NX three-dimensional modeling software;
(2) Determining normal rotation rated operating parameters, reverse rotation rated operating parameters and gas switching transition operating parameters of double-layer turbine blades in the reversing gas turbine, wherein the normal rotation rated operating parameters, the reverse rotation rated operating parameters and the gas switching transition operating parameters comprise gas temperature T, gas pressure P and rated rotating speed n of positions of the double-layer turbine blades;
(3) Calculating the forward running working condition, namely, the gas distribution baffle is in a complete open state, gas completely flows through the lower-layer blades, the gas drives the double-layer turbine blades to rotate forward, and no gas flows through the upper-layer blades;
(4) The reverse running condition calculation is that the gas distribution baffle is in a complete furling state, gas completely flows through the upper layer blades, the gas drives the double-layer turbine blades to reversely rotate, and no gas flows through the lower layer blades;
(5) Calculating the transition working condition of gas switching, namely, the gas distribution baffle is in a middle transition state, and part of gas flows through the lower layer blades and the upper layer blades;
(6) Under three working conditions, the strength of all positions of the double-layer turbine blade is checked respectively, the material endurance strength is used as an index, the ratio of the material endurance strength to the maximum equivalent stress in the blade is small and 1.3, if the requirements are not met, the blade structure is optimally designed, and the optimized double-layer turbine blade is subjected to strength calculation again until the strength requirements are met.
The invention may further include:
1. the working condition calculation of the positive transfer operation in the step (3) is specifically as follows:
Firstly, establishing a fluid-solid coupling calculation model of an upper blade and air, introducing the calculation model into CFX fluid calculation software, completing grid division, setting boundary conditions, wherein the boundary conditions comprise blade materials, rotating speed, gas parameters and inlet and outlet pressures, completing friction heat generation analysis of the upper blade and the air, and obtaining temperature load and surface pressure load of the upper blade;
secondly, establishing a fluid-solid coupling calculation model of the lower-layer blade, the wheel disc and the fuel gas, leading the calculation model into CFX fluid calculation software to complete grid division, setting boundary conditions, wherein the boundary conditions comprise materials of the blade and the wheel disc, inlet temperature, inlet pressure, outlet pressure, rotating speed, wheel disc surface temperature and heat exchange coefficient, and completing fluid-solid coupling calculation to obtain temperature load and surface fuel gas pressure load of the lower-layer blade and wheel disc temperature load;
And (3) inputting temperature loads and pressure loads of the upper layer blade, the lower layer blade and the wheel disc into strength calculation software ANSYS as boundaries, and simultaneously applying centrifugal loads, displacement constraints, pre-torsion constraints and wheel disc tenon tooth mortice constraints to a three-dimensional coupling model of the double-layer turbine blade and the wheel disc to finish strength coupling calculation of the double-layer turbine blade and the wheel disc.
2. The reverse running condition calculation in the step (4) is specifically as follows:
Firstly, establishing a fluid-solid coupling calculation model of a lower blade and air, introducing the calculation model into CFX fluid calculation software, completing grid division, setting boundary conditions, wherein the boundary conditions comprise blade materials, rotating speed, gas parameters and inlet and outlet pressures, completing friction heat generation analysis of the lower blade and air, and obtaining temperature load and surface pressure load of the lower blade 12;
Secondly, establishing a fluid-solid coupling calculation model of the upper layer blade, the wheel disc and the fuel gas, leading the calculation model into CFX fluid calculation software to complete grid division, setting boundary conditions, wherein the boundary conditions comprise materials of the blade and the wheel disc, inlet temperature, inlet pressure, outlet pressure, rotating speed, wheel disc surface temperature and heat exchange coefficient, and completing fluid-solid coupling calculation to obtain temperature load and surface fuel gas pressure load of the upper layer blade and wheel disc temperature load;
And (3) inputting temperature loads and pressure loads of the upper layer blade, the lower layer blade and the wheel disc into strength calculation software ANSYS as boundaries, and simultaneously applying centrifugal loads, displacement constraints, pre-torsion constraints and wheel disc tenon tooth mortice constraints to a three-dimensional coupling model of the double-layer turbine blade and the wheel disc to finish strength coupling calculation of the double-layer turbine blade and the wheel disc.
3. The transition condition calculation of the gas switching in the step (5) specifically comprises the following steps:
Firstly, when a gas distribution baffle is positioned at different positions, a fluid-solid coupling model of the gas, an upper blade and a lower blade is established, the fluid-solid coupling model is led into CFX software to complete flow calculation, the torque of the gas to the relative rotation center line of the upper blade and the lower blade is obtained, a torque balance point is determined, and the torque of the gas to the relative rotation center line of the upper blade and the lower blade is opposite in direction;
and secondly, under the state, the temperature load of the upper layer blade and the lower layer blade and the gas pressure load of the surface are taken as boundary conditions to be input into strength calculation software, and meanwhile, the constraint is applied to the three-dimensional coupling model of the double-layer turbine blade and the wheel disc, so that the strength coupling calculation of the double-layer turbine blade and the wheel disc is completed.
4. Under the working condition of forward running and the working condition of reverse running, the condition that fuel gas does not flow through one layer of blades exists, and at the moment, the influence of the friction heat generation of the blades and air stirring in a fuel gas channel on the temperature field of the double-layer turbine blade is considered, so that the influence on the strength of the double-layer turbine blade is further considered.
5. In the strength calculation, the influence of the gas switching transition working condition on the strength of the double-layer turbine blade is considered besides the forward running working condition and the reverse running working condition.
The method has the advantages that on the basis of the traditional single-layer blade strength assessment method, the special double-layer structure characteristics and the running environment characteristics of the double-layer turbine blade are considered, and the influence of the friction heat generation of the blade and air on the temperature field of the blade and the influence of the gas switching transition working condition on the double-layer turbine blade are considered in strength calculation. And the intensity calculation of the double-layer turbine blade is more comprehensive and accurate.
Drawings
FIG. 1 is a schematic diagram of a switching transition condition gas flow;
FIG. 2 is a schematic three-dimensional view of a double-layer turbine blade with counter-rotation;
FIG. 3 is a flow chart of the present invention;
FIG. 4 is a schematic illustration of a 1/N segmented double layer turbine blade and disk three-dimensional model.
Detailed Description
The invention is described in more detail below, by way of example, with reference to the accompanying drawings:
With reference to fig. 1-4, the core mechanism of the reversing gas turbine is shown in fig. 1, and mainly comprises a double-layer turbine blade 1, a double-layer guide vane 2, a wheel disc 3, a turbine shaft 4, an electric cylinder 5, a crank-link mechanism 6, a diversion channel 7, a gas distribution baffle 8 and a casing 9. The three-dimensional structure of the double-layer turbine blade 1 is shown in fig. 2, and mainly comprises an upper layer blade 10, a blade connecting section 11, a lower layer blade 12 and a tenon tooth 13. The gas distribution baffle 8 can be driven to rotate around the point A through the electric cylinder 5 and the crank connecting rod mechanism 6, when the gas distribution baffle 8 is at the uppermost end, the gas can only pass through the lower-layer channel, the gas drives the double-layer turbine blade 1 to rotate positively, when the gas distribution baffle 8 is at the lowermost end, the gas can only pass through the upper-layer channel, the gas drives the double-layer turbine blade 1 to rotate reversely, when the gas distribution baffle 8 is at the middle transition position, a part of the gas flows through the upper-layer channel, the gas generates reverse moment to the upper-layer blade 10, a part of the gas flows through the lower-layer channel, the gas generates forward moment to the lower-layer blade 12, and when the gas distribution baffle 8 is at a certain position, the gas generates equal and opposite moment to the upper-layer blade 10 and the lower-layer blade 12, and is in a moment balance state.
The method for checking the strength of the double-layer turbine blade with the reverse rotation function in the embodiment is shown in a flow chart in fig. 3, and comprises the following steps:
Step one, a three-dimensional coupling model of the double-layer turbine blade 1 and the wheel disc 3 is established in NX three-dimensional modeling software, and in order to simplify the calculation workload, the double-layer turbine blade 1 and the wheel disc 3 with 1/N sections are taken as models for subsequent strength calculation (N is the number of blades of the lower-layer blade 12).
Step two, determining normal rotation rated operating parameters, reverse rotation rated operating parameters and gas switching transition operating parameters of the double-layer turbine blade 1 in the reversing gas turbine, wherein the operating parameters comprise gas temperature T, gas pressure P, rated rotating speed n and the like of the position of the double-layer turbine blade.
And step three, calculating the working condition of positive transportation, namely the gas distribution baffle plate 8 is in a complete open state, gas completely flows through the lower layer blades 12, the gas drives the double-layer turbine blades 1 to rotate positively, and no gas flows through the positions of the upper layer blades 10.
Firstly, a fluid-solid coupling calculation model of the upper blade 10 and air is established, the calculation model is imported into CFX fluid calculation software to complete grid division, boundary conditions (the boundary conditions comprise blade materials, rotating speed, gas parameters, inlet and outlet pressures and the like) are set, and friction heat generation analysis of the upper blade 10 and air is completed to obtain temperature load and surface pressure load of the upper blade 10.
Secondly, a fluid-solid coupling calculation model of the lower-layer blades 12 and the wheel disc 3 and fuel gas is built, the calculation model is led into CFX fluid calculation software to complete grid division, boundary conditions (the boundary conditions mainly comprise materials of the blades and the wheel disc, inlet temperature, inlet pressure, outlet pressure, rotating speed, wheel disc surface temperature and heat exchange coefficient) are set, fluid-solid coupling calculation is completed, and temperature load and surface fuel gas pressure load of the lower-layer blades 12 and temperature load of the wheel disc 3 are obtained.
And (3) inputting temperature loads and pressure loads of the upper layer blade 10, the lower layer blade 12 and the wheel disc 3 into strength calculation software ANSYS as boundaries, and simultaneously applying centrifugal loads, displacement constraints, pre-torsion constraints and wheel disc tenon and mortise constraints to the three-dimensional coupling model of the double-layer turbine blade 1 and the wheel disc 3 to finish strength coupling calculation of the double-layer turbine blade 1 and the wheel disc 3.
And step four, calculating the reverse running condition, namely, the gas distribution baffle plate 8 is in a fully folded state, gas completely flows through the upper layer blades 10, the gas drives the double-layer turbine blades 1 to reversely rotate, and no gas flows through the lower layer blades 12.
Firstly, a fluid-solid coupling calculation model of the lower blade 2 and air is established, the calculation model is imported into CFX fluid calculation software to complete grid division, boundary conditions (the boundary conditions comprise blade materials, rotating speed, gas parameters, inlet and outlet pressures and the like) are set, friction heat generation analysis of the lower blade 12 and air is completed, and temperature load and surface pressure load of the lower blade 12 are obtained.
Secondly, a fluid-solid coupling calculation model of the upper layer blade 10, the wheel disc 3 and the fuel gas is established, the calculation model is imported into CFX fluid calculation software to complete grid division, boundary conditions (the boundary conditions mainly comprise materials of the blade and the wheel disc, inlet temperature, inlet pressure, outlet pressure, rotating speed, wheel disc surface temperature and heat exchange coefficient) are set, fluid-solid coupling calculation is completed, and temperature load and surface fuel gas pressure load of the upper layer blade 10 and temperature load of the wheel disc 3 are obtained.
And (3) inputting temperature loads and pressure loads of the upper layer blade 10, the lower layer blade 12 and the wheel disc 3 into strength calculation software ANSYS as boundaries, and simultaneously applying centrifugal loads, displacement constraints, pre-torsion constraints and wheel disc tenon and mortise constraints to the three-dimensional coupling model of the double-layer turbine blade 1 and the wheel disc 3 to finish strength coupling calculation of the double-layer turbine blade 1 and the wheel disc 3.
And step five, calculating the transition condition of gas switching, namely, the gas distribution baffle plate 8 is in an intermediate transition state, and part of gas flows through the lower layer blades 12 and part of gas flows through the upper layer blades 10.
Firstly, when the gas distribution baffle plate 8 is positioned at different positions, a fluid-solid coupling model of the gas and the upper blade 10 and the lower blade 12 is established, the fluid-solid coupling model is led into CFX software to complete flow calculation, the torque of the gas to the relative rotation center line of the upper blade 10 and the lower blade 12 is obtained, a torque balance point is determined, and at the moment, the torque of the gas to the relative rotation center line of the upper blade 10 and the lower blade 12 is opposite in size.
Secondly, in this state, the temperature load of the upper blade 10 and the lower blade 12 and the gas pressure load of the surface are input into the strength calculation software as boundary conditions, and simultaneously, the constraint is applied to the three-dimensional coupling model of the double-layer turbine blade 1 and the wheel disc 3, so that the strength coupling calculation of the double-layer turbine blade 1 and the wheel disc 3 is completed.
And step six, respectively carrying out strength assessment on all positions of the double-layer turbine blade 1 under three working conditions, and carrying out assessment by taking the material endurance strength as an index, wherein the ratio of the material endurance strength to the maximum equivalent stress in the blade is smaller than 1.3. If the requirements are not met, the blade structure should be optimally designed, and the optimized double-layer turbine blade 1 should be subjected to strength calculation again until the strength requirements are met.
The method has the following beneficial effects that on the basis of the traditional single-layer blade strength assessment method, the special double-layer structure characteristics and the running environment characteristics of the double-layer turbine blade are considered, and the influence of the friction heat generation of the blade and air on the temperature field of the blade and the influence of the gas switching transition working condition on the double-layer turbine blade are considered in strength calculation. And the intensity calculation of the double-layer turbine blade is more comprehensive and accurate.
Claims (3)
1. A double-layer turbine blade strength assessment method with a reverse rotation function is characterized by comprising the following steps of:
(1) Establishing a three-dimensional coupling model of the double-layer turbine blade and the wheel disc in NX three-dimensional modeling software;
(2) Determining normal rotation rated operating parameters, reverse rotation rated operating parameters and gas switching transition operating parameters of double-layer turbine blades in the reversing gas turbine, wherein the normal rotation rated operating parameters, the reverse rotation rated operating parameters and the gas switching transition operating parameters comprise gas temperature T, gas pressure P and rated rotating speed n of positions of the double-layer turbine blades;
(3) Calculating the forward running working condition, namely, the gas distribution baffle is in a complete open state, gas completely flows through the lower-layer blades, the gas drives the double-layer turbine blades to rotate forward, and no gas flows through the upper-layer blades;
(4) The reverse running condition calculation is that the gas distribution baffle is in a complete furling state, gas completely flows through the upper layer blades, the gas drives the double-layer turbine blades to reversely rotate, and no gas flows through the lower layer blades;
(5) Calculating the transition working condition of gas switching, namely, the gas distribution baffle is in a middle transition state, and part of gas flows through the lower layer blades and the upper layer blades;
The transition working condition calculation of gas switching specifically comprises the following steps:
Firstly, when a gas distribution baffle is positioned at different positions, a fluid-solid coupling model of the gas, an upper blade and a lower blade is established, the fluid-solid coupling model is led into CFX software to complete flow calculation, the torque of the gas to the relative rotation center line of the upper blade and the lower blade is obtained, a torque balance point is determined, and the torque of the gas to the relative rotation center line of the upper blade and the lower blade is opposite in direction;
secondly, under the state, the temperature load of the upper layer blade and the lower layer blade and the gas pressure load of the surface are used as boundary conditions to be input into strength calculation software, and meanwhile, constraint is applied to a three-dimensional coupling model of the double-layer turbine blade and the wheel disc, so that strength coupling calculation of the double-layer turbine blade and the wheel disc is completed;
(6) Under three working conditions, respectively carrying out strength assessment on all positions of the double-layer turbine blade, carrying out assessment by taking the material endurance strength as an index, wherein the ratio of the material endurance strength to the maximum equivalent stress in the blade is less than 1.3, and if the requirements are not met, carrying out optimal design on the blade structure, and carrying out strength calculation on the optimized double-layer turbine blade again until the strength requirements are met;
Under the working condition of forward running and the working condition of reverse running, the condition that fuel gas does not flow through one layer of blades exists, and at the moment, the influence of the friction heat generation of the blades and air stirring in a fuel gas channel on the temperature field of the double-layer turbine blade is considered, so that the influence on the strength of the double-layer turbine blade is further considered.
2. The method for evaluating the strength of the double-layer turbine blade with the reverse rotation function according to claim 1, wherein the calculation of the forward running operation condition in the step (3) is specifically as follows:
Firstly, establishing a fluid-solid coupling calculation model of an upper blade and air, introducing the calculation model into CFX fluid calculation software, completing grid division, setting boundary conditions, wherein the boundary conditions comprise blade materials, rotating speed, gas parameters and inlet and outlet pressures, completing friction heat generation analysis of the upper blade and the air, and obtaining temperature load and surface pressure load of the upper blade;
secondly, establishing a fluid-solid coupling calculation model of the lower-layer blade, the wheel disc and the fuel gas, leading the calculation model into CFX fluid calculation software to complete grid division, setting boundary conditions, wherein the boundary conditions comprise materials of the blade and the wheel disc, inlet temperature, inlet pressure, outlet pressure, rotating speed, wheel disc surface temperature and heat exchange coefficient, and completing fluid-solid coupling calculation to obtain temperature load and surface fuel gas pressure load of the lower-layer blade and wheel disc temperature load;
And (3) inputting temperature loads and pressure loads of the upper layer blade, the lower layer blade and the wheel disc into strength calculation software ANSYS as boundaries, and simultaneously applying centrifugal loads, displacement constraints, pre-torsion constraints and wheel disc tenon tooth mortice constraints to a three-dimensional coupling model of the double-layer turbine blade and the wheel disc to finish strength coupling calculation of the double-layer turbine blade and the wheel disc.
3. The method for evaluating the strength of the double-layer turbine blade with the reverse rotation function according to claim 1, wherein the calculation of the reverse rotation operation condition in the step (4) is specifically as follows:
Firstly, establishing a fluid-solid coupling calculation model of a lower blade and air, introducing the calculation model into CFX fluid calculation software, completing grid division, setting boundary conditions, wherein the boundary conditions comprise blade materials, rotating speed, gas parameters and inlet and outlet pressures, completing friction heat generation analysis of the lower blade and air, and obtaining temperature load and surface pressure load of the lower blade 12;
Secondly, establishing a fluid-solid coupling calculation model of the upper layer blade, the wheel disc and the fuel gas, leading the calculation model into CFX fluid calculation software to complete grid division, setting boundary conditions, wherein the boundary conditions comprise materials of the blade and the wheel disc, inlet temperature, inlet pressure, outlet pressure, rotating speed, wheel disc surface temperature and heat exchange coefficient, and completing fluid-solid coupling calculation to obtain temperature load and surface fuel gas pressure load of the upper layer blade and wheel disc temperature load;
And (3) inputting temperature loads and pressure loads of the upper layer blade, the lower layer blade and the wheel disc into strength calculation software ANSYS as boundaries, and simultaneously applying centrifugal loads, displacement constraints, pre-torsion constraints and wheel disc tenon tooth mortice constraints to a three-dimensional coupling model of the double-layer turbine blade and the wheel disc to finish strength coupling calculation of the double-layer turbine blade and the wheel disc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211534136.1A CN116006327B (en) | 2022-12-01 | 2022-12-01 | A strength assessment method for double-layer turbine blades with reverse rotation function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211534136.1A CN116006327B (en) | 2022-12-01 | 2022-12-01 | A strength assessment method for double-layer turbine blades with reverse rotation function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116006327A CN116006327A (en) | 2023-04-25 |
| CN116006327B true CN116006327B (en) | 2025-06-17 |
Family
ID=86018217
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211534136.1A Active CN116006327B (en) | 2022-12-01 | 2022-12-01 | A strength assessment method for double-layer turbine blades with reverse rotation function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116006327B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119714899B (en) * | 2024-12-25 | 2025-10-17 | 哈尔滨工程大学 | Gas turbine double-duct air inlet switching mechanism test bed, method, program and storage medium |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116006271A (en) * | 2022-12-01 | 2023-04-25 | 中国船舶重工集团公司第七0三研究所 | Turbine blade design method with reverse rotation function |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2006144869A (en) * | 2004-05-17 | 2008-06-27 | Л. Джеймс Мл. КАРДАРЕЛЛА (US) | TURBINE HOUSING STRENGTHENING IN A GAS-TURBINE JET ENGINE |
| JP4459943B2 (en) * | 2006-10-19 | 2010-04-28 | 株式会社日立製作所 | gas turbine |
| CN103604587A (en) * | 2013-08-27 | 2014-02-26 | 杭州海罗马科技有限公司 | High-speed rotation testing machine and method for testing high-speed rotation strength performance of rotor |
| CN205532725U (en) * | 2016-04-19 | 2016-08-31 | 中国船舶重工集团公司第七�三研究所 | A two movable vane structures are taken to turbine binary channels no. 1 of can backing a car for gas turbine |
| CN105756722B (en) * | 2016-04-22 | 2017-10-24 | 中国船舶重工集团公司第七�三研究所 | Can the through-flow switching valve of backing turbine |
| CN205503193U (en) * | 2016-04-22 | 2016-08-24 | 中国船舶重工集团公司第七�三研究所 | Turbine of can backing a car is with double -deck whole quiet bucket ring |
| RU182026U1 (en) * | 2017-12-18 | 2018-07-31 | Публичное Акционерное Общество "Одк-Сатурн" | TWO-TIER TURBINE DRIVER SHOVEL |
| CN109446592B (en) * | 2018-10-09 | 2020-02-07 | 湘潭大学 | Method for evaluating application effect of thermal barrier coating of turbine blade |
| CN109667625A (en) * | 2019-02-01 | 2019-04-23 | 中国船舶重工集团公司第七0三研究所 | It is a kind of for can backing turbine windage loss test cantilever rotor |
-
2022
- 2022-12-01 CN CN202211534136.1A patent/CN116006327B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116006271A (en) * | 2022-12-01 | 2023-04-25 | 中国船舶重工集团公司第七0三研究所 | Turbine blade design method with reverse rotation function |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116006327A (en) | 2023-04-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Ainley | Performance of axial-flow turbines | |
| Howell | Design of axial compressors | |
| CN114186506B (en) | Method for predicting full characteristic curve of centrifugal pump | |
| CN111062124A (en) | A Similar Modeling Method for Supercritical Carbon Dioxide Compressor Test | |
| CN111859563B (en) | Similar modeling method for supercritical carbon dioxide turbine test | |
| CN116006327B (en) | A strength assessment method for double-layer turbine blades with reverse rotation function | |
| US12305658B2 (en) | Performance test bench device for centrifugal compressor under variable working condition of engine | |
| CN114756978A (en) | Through-flow load design method for high-pressure compressor of simple-circulation marine gas turbine | |
| CN117010099A (en) | A cross-generation small bypass ratio turbofan engine high and low pressure turbine matching design method | |
| CN105864097B (en) | A multi-objective fuzzy hydraulic optimization design method for nuclear main pump impeller | |
| CN113705128A (en) | Wind turbine power modeling method based on state curve analysis | |
| CN109635512A (en) | A kind of centrifugal impeller inlet design method based on Correction and Control equation | |
| Avşar et al. | Aerodynamic design and performance optimization of a centrifugal fan impeller | |
| Zhao et al. | Performance analysis of embedded tri-screw pump based on computational fluid dynamics | |
| Shanechi et al. | Optimisation of a high pressure ratio radial-inflow turbine: coupled CFD-FE analysis | |
| Salameh et al. | Experimental study of automotive turbocharger turbine performance maps extrapolation | |
| Tian et al. | Performance and Loss Analysis of a Small‐Scale Supercritical CO2 Turbine | |
| CN114544133A (en) | A Similar Method of Turbine Variable Working Fluid Test | |
| CN108266234A (en) | A kind of industrial steam turbine high efficiency drum grade stator blade | |
| Wang et al. | Variable tandem stator geometric features on fan performance | |
| Niu et al. | Gas-dynamics design of reversible turbine for marine gas turbine engine | |
| CN120086998B (en) | Digital design method for high-load fan/compressor | |
| Yan et al. | The effects of the number of blades/vanes on the performance of a two-stage centrifugal compressor: The CFD analysis | |
| Sajedin et al. | Aero-structural study on the blade thickness effects in an automotive turbocharger turbine in transonic conditions | |
| Liu et al. | Investigation of flow field simulation and pulsation performance of non-circular gear hydraulic motor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |