A Rapid Method for Modeling a Variable Cycle Engine

Podsumowanie

Here, we present a protocol to build a component-level mathematical model for a variable cycle engine.

Streszczenie

The variable cycle engines (VCE) that combine the advantages of turbofan and turbojet engines, are widely considered to be the next generation aircraft engines. However, developing VCE requires high costs. Thus, it is essential to build a mathematical model when developing an aircraft engine, which may avoid a large number of real tests and reduce the cost dramatically. Modeling is also crucial in control law development. In this article, based on a graphical simulation environment, a rapid method for modeling a double bypass variable cycle engine using object-oriented modeling technology and modular hierarchical architecture is described. Firstly, the mathematical model of each component is built based on the thermodynamic calculation. Then, a hierarchical engine model is built via the combination of each component mathematical model and the N-R solver module. Finally, the static and dynamic simulations are carried out in the model and the simulation results prove the effectiveness of the modeling method. The VCE model built through this method has the advantages of clear structure and real-time observation.

Wprowadzenie

Modern aircraft demands bring great challenges to the propulsion system, which need more intelligent, more efficient or even more versatile aircraft engines¹. Future military propulsion systems also require both higher thrust at high speed and lower specific fuel consumption at low speed^1,2,3,4. In order to meet the technical requirements of future flight missions, General Electric (GE) put forward the variable cycle engine (VCE) concept in 1955⁵. A VCE is an aircraft engine that can perform different thermodynamic cycles by changing the geometry size or position of some components⁶. The Lockheed SR-71 "Blackbird" powered by a J58 turboramjet VCE has held the world record for the fastest air-breathing manned aircraft since 1976⁷. It also proved many potential advantages of supersonic flight. In the past 50 years, GE has improved and invented several other VCEs, including a double bypass VCE⁸, a controlled pressure ratio engine⁹ and an adaptive cycle engine¹⁰. These studies involved not only the general structure and performance verification, but also the control system of the engine¹¹. These studies have proven that the VCE can work like a high bypass ratio turbofan at subsonic flight and like a low bypass ratio turbofan, even like a turbojet at supersonic flight. Thus, the VCE can realize performance matching under different flight conditions.

When developing a VCE, a large amount of necessary verification works will be carried out. It may cost a large amount of time and outlay if all these works are performed in a physical way¹². Computer simulation technology, which has already been adopted in developing a new engine, can not only reduce the cost greatly, but also avoid the potential risks^13,14. Based on computer simulation technology, the development cycle of an engine will be reduced to nearly half, and the number of equipment required will be reduced dramatically¹⁵. On the other hand, simulation also plays an important role in the analysis of the engine behavior and control law development. For simulating the static design and off-design performance of engines, a program called GENENG¹⁶ was developed by the NASA Lewis Research Center in 1972. Then the research center developed DYNGEN¹⁷ derived from GENENG, and DYNGEN could simulate the transient performance of a turbojet and the turbofan engines. In 1989, NASA put forward a project, called Numerical Propulsion System Simulation (NPSS), and it encouraged researchers to construct a modular and flexible engine simulation program through the use of object-oriented programming. In 1993, John A. Reed developed the Turbofan Engine Simulation System (TESS) based on the Application Visualization System (AVS) platform through object-oriented programing¹⁸.

Meanwhile, rapid modeling based on graphical programming environment is being used gradually in simulation. The Toolbox for the Modeling and Analysis of Thermodynamic Systems (T-MATS) package developed by NASA is based on Matlab/Simulink platform. It is open source and allows users to customize built-in component libraries. T-MATS offers a friendly interface to users and it is convenient to analyze and design the built-in JT9D model¹⁹.

In this article, the dynamic model of a type of VCE has been developed here using Simulink software. The modeling object of this protocol is a double bypass VCE. Its schematic layout is shown in Figure 1. The engine can work in both single and double bypass modes. When the Mode Select Valve (MSV) is open, the engine performs better at subsonic conditions with a relatively large bypass ratio. When the Mode Select Valve is closed, the VCE has a small bypass ratio and a better supersonic mission adaptability. To further quantize performance of the engine, a double bypass VCE model is built based on component-level modeling method.

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Protokół

1. Preparation before modeling

1. Obtain design point performance.
   1. Open Gasturb 13. Select Variable Cycle Engine.
   2. Click on Basic Thermodynamics. Select Cycle Design. Open DemoVarCyc.CVC.
   3. Obtain the engine design point performance. These are shown on the right side of the window.
2. Obtain component maps.
   1. Open Gasturb 13. Select Variable Cycle Engine.
   2. Click on Off Design. Select Standard Maps. Open DemoVarCyc.CVC.
   3. Click on Off Design Point. Then select LPC, IPC, HPC, HPT and LPT; thus, all components maps are obtained.

2. Model each component of the VCE^20,21,22

1. Model a single component of a VCE. Take the high-pressure compressor as an example.
   1. Open Matlab. Click on Simulink. Double click on Blank Model.
   2. Click on Library, and place function to model.
   3. Double click on Function. According to the working principle of the compressor, the thermodynamic equation of the compressor is described. Then describe the equation with the MATLAB function.
   4. After finishing the MATLAB function, obtain the input and output of the compressor.
   5. Use Subsystem to mask the module. Then rename it with “compressor”. Thus far, a subsystem module called “compressor” is established.
2. Use the same steps to get the subsystems of all components including inlet, fan, duct, core driven fan stage(CDFS), bypass mixer, compressor, burner, high-pressure turbine, low-pressure turbine, mixer, afterburner and nozzle.
   1. Combine output of each component with input of the next component.

3. Solution of the whole model

1. Construct dynamic co-working equations of whole model.
   1. Construct dynamic co-working equations. Construct the following 6 independent co-working equations.
   2. Determine the flow balance equation for inlet and outlet of burner:
      W_a3: compressor outlet section air flow, W_f: burner fuel flow, W_g44: high-pressure turbine inlet gas flow.
   3. Determine the flow balance equation for inlet and outlet of low-pressure turbine:
      W_g44: low-pressure turbine inlet section gas flow, W_g5: low-pressure turbine outlet gas flow.
   4. Determine the flow balance equation for inlet and outlet of nozzle:
      W_g7: nozzle inlet gas flow, W_g9: nozzle outlet gas flow.
   5. Determine the static pressure balance equation for inlet of rear mixer:
      P_s163: static pressure of main outer bypass outlet, P_s63: static pressure of inner bypass outlet.
   6. Determine the flow balance equation of fan inlet and outlet:
      W_a2: fan inlet air flow, W_a21: CDFS inlet air flow, W_a13: sub-outer bypass inlet air flow
   7. Determine the flow balance equation of CDFS outlet:
      W_a21: CDFS inlet air flow, W_a125: CDFS bypass inlet air flow, W_a25: compressor inlet air flow.
   8. The above 6 independent equations constitute the following equations.
      
2. Use the N-R iteration solver in TMATS to solve the above equations.
   1. Before using the solver to solve the co-working equations, set the N-R iteration solver. According to the modeling process, select the following 6 initial guesses: component map auxiliaries line of fan, CDFS, high-pressure compressor, high-pressure turbine and low-pressure turbine β₁, β₂, β₃, β₄, β₅, sub-outer bypass inlet flow.

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Wyniki

In order to prove the validity of the simulation model, several typical performance parameters selected in static and dynamic simulations are compared with the data in Gasturb.

In a static simulation, we compare several key performance parameters of the model with these parameters in Gasturb to verify the accuracy of the static model. Table 2 shows the result of the comparison at the design point with H=0 m, M_a=0, W_f=0.79334 kg/s under a double bypass ope...

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Dyskusje

Based on a graphical simulation environment, a VCE component-level model can be built rapidly through modular hierarchical architecture and object-oriented modeling technology. It offers a friendly interface to users and it is convenient to analyze and design the model¹⁹.

The main limitation of this method is the execution efficiency of the model. Because the model is written in scripting language, the model needs to be recompiled every time it runs. Thus, the execution...

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Materiały

Name	Company	Catalog Number	Comments
Gasturb	GasTurb GmbH	Gasturb 13
MATLAB	MathWorks	R2017b
TMATS	NASA	1.2.0