CN107194028B - Blade design method for RAT - Google Patents
Blade design method for RAT Download PDFInfo
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- CN107194028B CN107194028B CN201710256333.4A CN201710256333A CN107194028B CN 107194028 B CN107194028 B CN 107194028B CN 201710256333 A CN201710256333 A CN 201710256333A CN 107194028 B CN107194028 B CN 107194028B
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Abstract
The invention belongs to the technology of a ram air turbine system, and particularly relates to a blade design method for an RAT (RAT). The method comprises the following steps of designing parameters including two-dimensional airfoil profile, airfoil chord length, blade extension and blade torsion angle: selecting and adopting CFD simulation to obtain airfoil aerodynamic performance data from the existing airfoil data according to the emergency power requirement of the airplane, and obtaining a basic airfoil; calculating according to a phylloton-momentum theory to obtain an airfoil chord length and a blade torsion angle, and optimizing by adopting a genetic algorithm; the blade elongation was calculated according to the following formula
Wherein C isPFor the turbine power extraction coefficient, ρ is the air density, v is the incoming flow velocity, and W is the required power. The invention provides a cyclic iterative optimization design method of RAT blades, which combines a phyllotactic factor-momentum theory, CFD simulation and genetic algorithm, and the performance of the designed RAT blades is rapidly evaluated by utilizing a calculation formula formed by actually used data, so that the calculation speed of the RAT blade design is improved.
Description
Technical Field
The invention belongs to the technology of a ram air turbine system, and particularly relates to a blade design method for an RAT (RAT).
Background
The ram air turbine system is mainly used as an emergency power system of the airplane and provides emergency hydraulic energy or (and) emergency electric energy for the airplane, so that the maneuverability of a normal flying attitude of the airplane can be still maintained under the condition that the main power of the airplane is lost. At present, ram air turbine blades independently developed in China are mostly obtained by modifying existing blades, the flow of a traditional RAT blade design method is one-way, the relation among all design parameters is not clear, the design process is complicated and repeated, the design period is long, and the designed blade power extraction efficiency is low.
With the increasing of the power-to-weight ratio requirements of advanced airplanes on the RAT system, the improvement of the RAT blade power extraction efficiency is an important research field in the future RAT system development.
Disclosure of Invention
The technical problem solved by the invention is as follows: a blade design method for a RAT is provided to better meet the requirement of advanced airplanes on a high power-to-weight ratio RAT system in the future.
The technical scheme of the invention is as follows: a blade design method for RAT is characterized in that: the method comprises the following steps of designing parameters including two-dimensional airfoil profile, airfoil chord length, blade extension and blade torsion angle:
selecting and adopting CFD simulation to obtain airfoil aerodynamic performance data from the existing airfoil data according to the emergency power requirement of the airplane, and obtaining a basic airfoil;
calculating according to a phylloton-momentum theory to obtain an airfoil chord length and a blade torsion angle, and optimizing by adopting a genetic algorithm;
the blade extension D is calculated according to the following formula:
wherein C isPFor the turbine power extraction coefficient, ρ is the air density, v is the incoming flow velocity, and W is the required power.
Preferably, aerodynamic performance data of the airfoil profile within an attack angle range of-5 degrees to 80 degrees is obtained through CFD simulation, and a basic airfoil profile is selected.
Preferably, the turbine power extraction coefficient CPTaking 0.18-0.21.
Preferably, the airfoil chord length and the blade twist angle are calculated according to the following method:
step 5, performing rapid pneumatic performance evaluation on each variable combination, and repeating the steps 1-3;
step 6, analyzing and optimizing results of all leaf data by adopting a genetic algorithm according to input conditions;
and 7, judging whether the optimization result meets the requirement, if not, resetting the optimization variable, and performing iterative solution until an optimal blade scheme is obtained.
The invention has the beneficial effects that: the invention provides a cyclic iterative optimization design method of RAT blades, which combines a phyllotactic factor-momentum theory, CFD simulation and genetic algorithm, and the performance of the designed RAT blades is rapidly evaluated by utilizing a calculation formula formed by actually used data, so that the calculation speed of the RAT blade design is improved. In addition, test data is adopted for checking the CFD simulation model adopted in the design process, and the accuracy of the designed result is high. The design process adopts a loop iteration mode instead of a one-way design flow, and the power extraction efficiency of the RAT blade obtained by design is high. The method can provide powerful support for the emergency strategy formulation and the comprehensive energy allocation of the airplane, and has a positive effect on improving the market competitiveness of the domestic independently-developed ram air turbine system.
Drawings
FIG. 1 is a schematic diagram of a RAT blade configuration;
FIG. 2 is a block flow diagram of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the following embodiments.
Referring to fig. 1 and 2, in the RAT blade design method according to the present invention, the design parameters include a two-dimensional airfoil 1, an airfoil chord length 2, a blade extension 3, and a blade twist angle 4.
The blade extension 3 is comprehensively determined according to the emergency power requirement and the space weight requirement of the airplane, and the size of the blade extension directly determines the upper limit of the power which can be provided by the RAT (radio access technology) due to the limit value of the power extraction efficiency. The preliminary selection method of the leaf extension 3 is determined according to the following formula:
wherein C isPThe turbine power extraction coefficient is generally 0.18-0.21, rho is air density, v is incoming flow velocity, and W is required power.
The two-dimensional wing profile 1 is a basic element of a blade section, a plurality of wing profiles are selected from existing wing profile data according to the emergency power requirement and the use condition characteristics of an airplane, CFD modeling simulation calculation is carried out on the wing profiles, aerodynamic performance data of the two-dimensional wing profiles within a large attack angle range (-5-80 degrees) are obtained, the aerodynamic performance data comprise lift force, resistance, lift-drag ratio, pressure distribution, separation stall attack angle and the like, analysis and comparison are carried out according to actual design requirements, and a basic wing profile is selected.
The airfoil chord length 2 and the blade torsion angle 4 are dimensional data of the two-dimensional airfoil 1 on each spanwise section of the three-dimensional blade, and respectively represent the airfoil chord length and the torsion angle of the airfoil at a specific spanwise section position, and the specific calculation and optimization method comprises the following steps: 1. firstly, dividing the blade into 10-30 sections along the spanwise direction, and obtaining initial values of airfoil chord length 2 and blade torsion angle 4 of each section according to a Wilson method; 2. calculating pneumatic data of each section by adopting a momentum-phyllotaxis theory; 3. performing integral addition on all the section pneumatic data to obtain the power extraction efficiency of the whole blade under different tip speed ratios; 4. setting the airfoil chord length 2 and the blade torsion angle 4 as optimization variables to generate a calculation population; 5. performing rapid pneumatic performance evaluation on each variable combination, and repeating the steps 1-3; 6. analyzing and optimizing results of all leaf data by adopting a genetic algorithm according to input conditions; 7. and judging whether the optimization result meets the requirement, if not, resetting the optimization variables, and performing iterative solution until an optimal blade scheme is obtained.
The method integrates the rapid performance evaluation calculation formula obtained by using the data statistical rule actually, and the design calculation efficiency is greatly improved compared with that of the traditional design method. Meanwhile, a genetic optimization algorithm is adopted, and an effective method is provided for calculating a multi-parameter matching optimal solution set of a complex system. The invention adopts loop iteration in the calculation, and simultaneously proves the simulation model by using the test data, and the design result is better than that of the traditional design method.
The blade design method for the RAT realizes the forward design idea of the RAT blade by combining the preliminary theoretical calculation, the high-performance simulation calculation, the multi-parameter joint optimization and the test result correction, and effectively improves the design speed of the RAT blade and the power extraction efficiency of the designed RAT blade. In addition, because the automatic curved surface generation fairing technology is adopted during modeling, the digital model is updated synchronously with the design parameters, the design efficiency is high, the manual modeling error is small, and the method has a great practical application value.
Claims (1)
1. A blade design method for RAT is characterized in that: the method comprises the following steps of designing parameters including two-dimensional airfoil profile, airfoil chord length, blade extension and blade torsion angle:
selecting the existing airfoil profile data according to the emergency power requirement of the airplane, acquiring aerodynamic performance data of the airfoil profile within an attack angle range of-5 degrees to 80 degrees by CFD simulation, and selecting a basic airfoil profile;
calculating according to a phylloton-momentum theory to obtain an airfoil chord length and a blade torsion angle, and optimizing by adopting a genetic algorithm; the method comprises the following steps:
step 1, dividing a blade into 10-30 sections along the spanwise direction, and obtaining initial values of airfoil chord lengths and blade torsion angles of the sections according to a Wilson method;
step 2, calculating pneumatic data of each section by adopting a momentum-phylline theory;
step 3, performing integral addition on all the section pneumatic data to obtain the power extraction efficiency of the whole blade under different tip speed ratios;
step 4, setting the airfoil chord length and the blade torsion angle as optimization variables to generate a calculation population;
step 5, performing rapid pneumatic performance evaluation on each variable combination, and repeating the steps 1-3;
step 6, analyzing and optimizing results of all leaf data by adopting a genetic algorithm according to input conditions;
step 7, judging whether the optimization result meets the requirement, if not, resetting the optimization variable, and performing iterative solution until an optimal blade scheme is obtained;
the blade extension D is calculated according to the following formula:
wherein CP is that the turbine power extraction coefficient is 0.18-0.21, ρ is the air density, v is the incoming flow velocity, and W is the required power.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102708266A (en) * | 2012-06-12 | 2012-10-03 | 中国科学院工程热物理研究所 | Method for predicting and calculating limit load of horizontal-axis wind turbine blade |
| CN104346500A (en) * | 2014-11-24 | 2015-02-11 | 沈阳化工大学 | Optimum design method for wind turbine blade |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US8651815B2 (en) * | 2010-03-22 | 2014-02-18 | Hamilton Sundstrand Corporation | Lightweight stow abort mechanism |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102708266A (en) * | 2012-06-12 | 2012-10-03 | 中国科学院工程热物理研究所 | Method for predicting and calculating limit load of horizontal-axis wind turbine blade |
| CN104346500A (en) * | 2014-11-24 | 2015-02-11 | 沈阳化工大学 | Optimum design method for wind turbine blade |
Non-Patent Citations (2)
| Title |
|---|
| 两型冲压空气涡轮翼型气动特性分析;王健 等;《探索 创新 交流——第六届中国航空学会青年科技论坛文集（上册）》;20140625;191-195 * |
| 冲压涡轮发电***数值分析及试验研究;*** 等;《第二届中国航空学会青年科技论坛文集》;20060501;235-241 * |
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