Available online at ScienceDirect. Procedia Engineering 150 (2016 )

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1 Available online at ScienceDirect Procedia Engineering 150 (2016 ) International Conference on Industrial Engineering, ICIE 2016 The Thermo-Gas-Dynamic Modeling of Afterburning Turbofan Engine for High Maneuverable Aircraft Combined with Its Automatics I.A. Krivosheev, D.G. Kozhinov, A.E. Kishalov, * Ufa State Aviation Technical University, K. Marx street, 12, Ufa, , Russian Federation Abstract The article considers modeling of aviation afterburning turbofan engine combined with its electrohydromechanical automatic control systems, supervision and diagnostics for high maneuverable aircraft. It describes an aviation engine and its automatic control system Dvig_Otladka2 developed based on Framework SAMCTO imitating simulation system. The designed imitation models sensors, regulators and actuating mechanism are described. A description of automatic control system action of one of modern aviation afterburning turbofan engine IV generation is presented; the change of main engine parameters by simulating of transient process of afterburner engagement and appearance on the augmented maximum rating are analyzed. The described technology of thermo-gas-dynamic simulation of aviation engines combined with its automatic control system allows selecting and optimizing the control and regulation programs considerably to accelerate fundamental phases of aviation engines design The Authors. Published by by Elsevier Ltd. Ltd. This is an open access article under the CC BY-NC-ND license ( Peer-review under responsibility of the organizing committee of ICIE Peer-review under responsibility of the organizing committee of ICIE 2016 Keywords: aviation engines; modeling aviation engines; automatic control systems; automatic aviation engine; engagement of afterburner; transient process; system imitation modeling; augmented rating 1. Introduction At the first phase of aviation turbojet engine projecting there are produced different thermo-gas-dynamic calculations, as a result of them it is realized selection and optimization of scheme, of operation principle, of main engine parameters and geometrical dimensions of air-gas channel by basic altitude-velocity regimes. Exactly at this stage of projecting it is very important to work out the engine control and regulation laws in details, course of its * Corresponding author. Tel.: address: kishalov@ufanet.ru The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license ( Peer-review under responsibility of the organizing committee of ICIE 2016 doi: /j.proeng

2 I.A. Krivosheev et al. / Procedia Engineering 150 ( 2016 ) dynamic processes. Only by such multiple-aspect interdisciplinary approach analysis, it is possible to design in short time final product with high characteristics of perfection, profitable behavior of operational description in the whole range of possible steady-state and transient processes [1]. It exists a number of software complexes for thermo-gasdynamic simulation and they are efficiently used on different phases of product life cycle practically by all big manufacturers [2 4]. Much less of software complexes for nodal simulating of aviation engines in common with action of their automatic control system (ACS), with possibility of automatic switching from one regulation program to another. One of this software is Dvig_Otladka [5], developed with help of MetaCAE/Framework SAMCTO [6] on the base of system of imitating modeling (SIM) Dvigwp [7 9]. Dvig_Otladka allows simulating of aviation engines and power plants on their base of different scheme and operational principles of transient-free and transient processes. Automated regulation system is presented by one structural element (SE) «Regulator», by various installation-specific settings of which operation of different automatic types can be imitated [10, 11]. The topological model of afterburning turbofan engine with integral model of ACS is introduced on Fig. 1 [12]. Nomenclature F nozzle throat G fuel n HP n LP n max p K T H T max control lever T area of nozzle throat fuel consumption in afterburner rotating frequency of low-pressure rotor rotating frequency of high-pressure rotor maximum frequency of rotating pressure after compressor ambient air temperature peak temperature setting angle of control lever pressure ratio of turbine Fig. 1. Topological model of afterburning turbofan engine in SIM Dvig_Otladka, where 1 ambient conditions; 2 input device; 3 low pressure compressor; 4 gases selection; 5 high pressure compressor; 6 gases selection 2; 7 combustor chamber; 8 air-to-air heat exchanger; 9 power selection; 10 power selection 2; 11 gases selection 3; 12 high pressure turbine; 13 low pressure turbine; 14 flow mixer; 15 afterburner; 16 jet nozzle; 17 regulator; 18 total result.

3 128 I.A. Krivosheev et al. / Procedia Engineering 150 ( 2016 ) For modeling of more wide spectrum of different regulators and provided by them regulation laws, it is developed SIM Dvig_Otladka2, in which integral automatic model was divided into smaller, but more universal SE, describing discrete systems and elements of automatic control system, control and diagnostics of aviation engine. Combination of various element sets, different settings of each individual SE can simulate work of engine automatic of different schemes and control laws [13]. 2. Modeling of afterburning turbofan engine of IV th generation In this work is shown modeling of modern afterburning turbofan engine for high maneuverable aircraft of IVth generation combined with its ACS (Fig. 2). For the engines with afterburner it is critical the transitional process of afterburner engagement, during which can begin the stalling and surging of compressor, the flame in afterburner can blow out [14, 15]. To prevent this ACS of engine, tracking rotors sloping, switches to other index of rotor slipping and regulates the area of nozzle throat while afterburner fuel ignition for a certain time. At the cost of this, engine decreases frequency of low pressure rotor rotating, decreases fuel consumption in the combustor chamber, increases reserves of aerodynamic stability of compressors, improves conditions of fuel combustion in afterburner [15 17]. Control of engine model and its ACS can be realized as the result of angel setting change of engine control lever (control lever, position 7 on Fig. 2). SE control lever, combined with hydro-moderated, passes information for other elements of automatic. Rotation frequency of high pressure rotor (physical or corrected) is supported versus ambient air temperature and setting angel of control lever (n HP = f( control lever, T H )). Maximal frequency of rotating (also physical or corrected) with ambient air temperature correction is tracked by SE Limiter of maximum parameters (mechanical) (n max = f(t H ), position 10). Value of maximal temperature of gases behind turbine is tracked by SE Limiter of maximum parameters (gas-dynamic), joint with SE Sensor, which simulates placing of sensors of different types with various characteristics and accuracy of installation (for example, T max = f(t H ), positions 12 and 1, respectively). Fig. 2. Topological model of afterburning turbofan engine for high maneuverable aircraft of IVth generation combined with its ACS in SIM Dvig_Otladka2, where 1 sensor; 2 regulator of afterburner fuel; 3 fuel manifolds; 4 mixer of information stream; 5 fuel supply; 6 regulator of T (mechanical); 7 control lever; 8 hot streak; 9 splitter of information streams; 10 limiter of maximum parameters (mechanical); 11 regulator pump; 12 limiter of maximum parameters (gas-dynamic). The mechanical and gas-dynamic limiters simulate the work of block of maximum regulators. Model is adjusted thus, that at the maximum regime the engine is controlled by block of maximum regulators (regulator pump is

4 I.A. Krivosheev et al. / Procedia Engineering 150 ( 2016 ) adjusted to the large value of rotating frequency). The regulator of T (position 6) tracks rotating frequency of low and high pressure rotor and versus in ambient air temperature regulates area of jet throat of convergentingdivergenting nozzle (n LP = f(t H, n HP ) and F nozzle throat = f(n LP )). At moment of afterburner fuel ignition, simulated with the help of SE hot streak (position 8), regulator changes to larger value of rotating frequency of low pressure rotor and «opens» jet nozzle. The fuel in afterburner is measured out versus pressure behind compressor with the help of SE Regulator of afterburner fuel (position 2), which distributes it to the fuel manifolds (position 3), determines limits of steady-state combustion and ignition of air-fuel mixture (G fuel /p K = f( control lever, T H )). With the help of varied installation-specific settings of SE automatic can get desired passing of and formulate demands for its individual elements [18]. Modeling results of transitional process afterburner engagement are shown in Fig Fig. 3. Control influence on the engine The time step by modeling is 0,01 second. When control lever transferring in range of augmented rating appears signal for completing of fuel manifolds afterburner 1 (starting), regulator of T changes to larger value of rotating frequency of low pressure rotor then appears signal for starting of hot streak (Fig. 5). If conditions of ignition of airfuel mixture in afterburner in zone of starting fuel manifold are met, happens ignition of afterburner and other fuel manifolds begin to be completing [19, 20]. 3. Conclusion Developed system of imitating simulation of aviation engine Dvig_Otladka2 contains a rich collection of structural elements for system modeling of automatic control of different modern aviation engines of various schemes and principles of operation. The main principle, inserted in simulating at that is the modeling of work elements of automatic and the influencing on the engine, and not the modeling of specific regulator or of actuating mechanism with its concrete arrangement and dimension type. Described technology of thermo-gas-dynamic modeling of aviation engine with its automatics makes it possible to analyze passing of different complex transition processes, to select and to optimize the control and regulation programs, it permits considerably to accelerate fundamental phases of modern aviation gas turbine engine designing and to avoid projecting arrows. The work is carried out with supporting of Ministry of education and science of Russian Federation.

5 130 I.A. Krivosheev et al. / Procedia Engineering 150 ( 2016 ) Fig. 4. Change of relative rotating frequency of rotor and gases temperature behind turbine in transitional process of afterburner starting Fig. 5. Change of relative area of nozzle throat, of fuel consumption and hot streak signal in transitional process of afterburner starting

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