Performance Simulation of Turboprop Engine Using SIMULINK® Model

Author(s):  
Changduk Kong ◽  
Hongsuk Roh

A performance simulation model of a turboprop engine, the PT6A-62, which is the power plant of KT-1, was developed to predict the steady-state behaviors using the SIMULINK® model. The SIMULINK model consists of subsystems to represent engine components such as intake, compressor, combustor, compressor turbine, power turbine and exhaust nozzle. For validation, performance parameters calculated using the SIMULINK model were compared with the results using GASTURB model. The steady-state performance analysis using the developed SIMULINK model was performed. Performance parameters, such as the mass flow rate, the compressor pressure ratio, the fuel flow rate, the specific fuel consumption ratio and the turbine inlet temperature, were conducted to evaluate validity of the SIMULINK model at various cases. The first case was the uninstalled condition at various altitudes from sea level to 9144m (30000ft) with fixed M.N. = 0. And the second case was the installed condition at various altitudes from sea level to 7620m (25000ft) with fixed M.N. = 0. The third case was the installed condition at altitudes of 1524m (5000ft) and 3048m (1000ft) and at the M.N. = 0.1, 0.2 and 0.3 in ECS operation ECS. In this investigation, it was confirmed that the results using the SIMULINK model were well agreed with the results using the GASTURB model within maximum 6.5%.

Author(s):  
Changduk Kong ◽  
Jayoung Ki

A performance simulation program for the turboprop engine (PT6A-62), which is the power plant of the first Korean indigenous basic trainer KT-1, was developed for more precise performance prediction, development of an EHMS (Engine Health Monitoring System) and the flight simulator. Characteristics of components including compressors, turbines, the combustor and the constant speed propeller were required for the steady state and transient performance analysis with on and off design point analysis. In most cases, these were substituted for what scaled from similar engine components’ characteristics with the scaling law. The developed program was evaluated with the performance data provided by the engine manufacturer and with analysis results of GASTURB program, which is well known for the performance simulation of gas turbines. Performance parameters such as mass flow rate, compressor pressure ratio, fuel flow rate, specific fuel consumption ratio and turbine inlet temperature were discussed to evaluate validity of the developed program at various cases. The first case was the sea level static standard condition and other cases were considered with various altitudes, flight velocities and part loads with the range between idle and 105% rotational speed of the gas generator. In the transient analysis, the Continuity of Mass Flow Method was utilized under the condition that mass stored between components is ignored and the flow compatibility is satisfied, and the Modified Euler Method was used for integration of the surplus torque. The transient performance analysis for various fuel schedules was performed. When the fuel step increase was considered, the overshoot of the compressor turbine inlet temperature occurred. However, in case of the fuel ramp increase longer than the fuel step increase, the overshoot of the compressor turbine inlet temperature was effectively reduced.


Author(s):  
Se Won Kim ◽  
Sang Kyoon Lee ◽  
Hee Cheon No

The effect of non-condensable gas on the subcooled water critical flow in a safety valve is investigated experimentally at various subcoolings with 3 different disk lifts. To evaluate its effect on the critical pressure ratio and critical flow rate, three parameters are considered: the ratios of outlet pressure to inlet pressure, the subcooling to inlet temperature, and the gas volumetric flow to water volumetric flow are 0.15–0.23, 0.07–0.12, and 0–0.8, respectively. It turns out that the critical pressure ratio is mainly dependent on the subcooling, and its dependency on the gas fraction and the pressure drop is relatively small. When the ratio of nitrogen gas volumetric flow to water volumetric flow becomes lower than 20%, the subcooled water critical flow rate is decreased about 10% compare to the water flow rate of without non-condensable gas. However, it maintains a constant value after the ratio of gas volumetric flow to water volumetric flow becomes higher than 20%. The subcooled water critical flow correlation, which considers subcooling, disc lift, backpressure, and non-condensable gas, shows good agreement with the total present experimental data with the root mean square error 8.17%.


1962 ◽  
Vol 2 (02) ◽  
pp. 156-164 ◽  
Author(s):  
H.D. Outmans

Abstract In steady vertical flow, the interface of an immiscible liquid-liquid displacement is horizontal for any flow rate below the critical in non-vertical flow, however, the shape of the interface in the steady state does depend on the flow rate, and the purpose of this paper is to calculate the unsteady interfaces during the transition of one steady state of flow to another. A knowledge of these transient interfaces is of considerable importance in reservoir engineering where the calculation of breakthrough recovery depends on the instant the interface reaches the producing wells and on the shape of the interface at that time. Although the emphasis is put on transient interfaces, which eventually approach stable equilibrium, it is shown that if the displacement exceeds a critical rate no equilibrium is possible. The interface is then unstable and viscous fingers are formed during the displacement. The critical rate and the shape of the transient and equilibrium interfaces are affected by the effective interfacial tension; but since this effective inter facial tension appears in the calculations only in combination with the in verse square of the thickness of the medium, its effect in the reservoir would appear to be negligible compared to its significance in model experiments. Introduction Stability criteria and the early growth of interfacial disturbances in a plane parallel to the boundaries of a dipping formation in which oil is displaced by an incompressible fluid were described in a previous paper. This type of instability is significant in thin reservoirs. However, if the reservoir has appreciable thickness, then interfacial stability in vertical planes, normal to the upper and lower boundaries, also becomes important (the displacement is supposed to be parallel to these vertical planes). The difference between the two stability problems is that, in the first case, the intersections of the interface with planes parallel to the boundaries are normal to the direction of the displacement; in the second case, the intersections, this time with vertical planes, are not normal to the displacement. Instead, they are tilted at an angle which depends on the displacement rate. The tilt of steady interfaces was calculated by Dietz who also determined the critical rate of displacement for stability in the vertical plane by assuming that this rate would coincide with an interfacial tilt equal to the dip of the formation. The critical rate thus calculated is the same as has been found for thin reservoirs (see Eq. 1.1 of Ref. 1 and of the present paper). Dietz's calculation of the stable tilt was verified by laboratory experiments and the agreement was found to be fairly good. It is doubtful, however, that stable tilts actually exist in the reservoir because a change in production rate is not followed by an instantaneous adjustment of the interface to the new rate but, rather, by a transition period during which the interface changes from one equilibrium tilt to the other. The principal objective of this paper has been to describe these transient interfaces without putting any restrictions on the flow conditions or the shape of the interface, as had been done previously. The second objective was to compute the critical velocity, taking into account capillary effects, and the third was to evaluate, at least qualitatively, the shape of the front at rates above the critical, again without making the simplifying assumptions introduced by previous investigators. In the following sections two examples are given of the calculation of interfacial motion. The first describes this motion for an initially horizontal interface in a dipping layer, and the second for a vertical interface in a horizontal layer. The mathematical formulation of the problem is non linear in the boundary conditions, and this prohibits its solution in closed form. Instead, the solution is obtained in the form of higher-order approximations. SPEJ P. 156^


Author(s):  
A. Marcellan ◽  
W. P. J. Visser ◽  
P. Colonna

There is a high potential for civil applications of Unmanned Aerial Vehicles (UAV) in areas such as goods transport, telecommunication, remote monitoring and sensing, surveillance, search and rescue, and disaster management. Developments in areas such as telecommunication, control and information technology offer opportunities for long range remotely or automatically piloted missions. This requires efficient and light-weight small propulsion systems. The potential of turboprop propulsion for civil UAVs using micro turbine technology has been explored and compared with existing concepts, such as piston engine driven propellers. Different propulsion concepts have been analyzed and the application areas where advanced turboprops would be superior to other systems such as reciprocating engines and electric motors, identified. However, turboprop engines of the small power capacity required for the aircraft concepts and missions considered are not currently available with competitive performance. A conceptual design study of a micro turboprop engine has been performed by downscaling an existing reference engine. Scale effects on efficiency have been taken into account, as well as effects of technological progress. Engine cycle optimization has been carried out and the effects of turbine inlet temperature, compressor pressure ratio, engine size, and component efficiency have been investigated. An aerodynamic and flight performance model of a baseline UAV has been developed in order to predict mission performance. This model has been coupled to a turboprop model to evaluate system performance with different engine configurations for the selected mission. The outcome of the study provides information about the technological improvements in terms of cycle efficiency required to make the micro-turboprop a competitive solution. The Propulsion and Power group of Delft University of Technology will pursue these R&D goals in an attempt to contribute to the development of civil UAV technology.


Author(s):  
Shiyao Li ◽  
Zhenlin Li ◽  
Ning Huang

Accurate performance simulation can provide operating parameters and performance parameters for the gas turbine’s optimization, maintenance, and fault diagnosis. However, the components maps necessary for performance simulation are not publically available. In addition, the same type of gas turbine has slightly different component operating characteristics due to components′ variations in status and assembly tolerance. These causes bring real difficulties to the research of performance simulation. In order to obtain accurate components characteristics and performance simulation results, the original or generic components maps should be modified by the scaling factors. In the process of calculating scaling factors, the simulation model is applied repeatedly to determine the engine’s actual performance parameters until the simulated gas path thermal parameters are compatible with the actual measureable data. This paper introduces a new adaptation method and substitutes the calculation model with the simulation model in the adaptation process. It directly calculates the mass flow rate, isentropic efficiency, and pressure ratio of compressor and turbine based on measureable parameters such as gas path temperature, pressure, fuel component and mass flow rate. Moreover, this paper introduces the virtual gas generator model that enhances the applicability of calculation model based performance adaptation method on gas generators with different structures. This method has been applied to GE PGT25+ gas generator (single-spool) and RR RB211-24G gas generator (double-spool). Compared with the simulation model used in adaptation process, performance calculation model is much simpler and less time consuming.


Author(s):  
S. M. Suleiman ◽  
Y. G. Li

Natural gas pipeline plays an important role in transporting natural gas over a long distance. Its performance and operating behavior are affected by many factors, such as ambient conditions, natural gas flow rate, operation and control of compressor pumping stations, etc. Better understanding of the performance and behavior of an integrated pipeline-compressor system used for gas transmission will be beneficial to both design and operation of natural gas pipelines. This paper introduces a novel steady-state thermodynamic performance simulation approach for natural gas pipelines based on fundamental thermodynamics with the inclusion of the coupling between a pipeline and compressor pumping stations. A pipeline resistance model, a compressor performance model characterized by an empirical compressor map and a pipeline control schedule for the operation of an integrated pipeline-compressor system are included in the simulation approach. The novel approach presented in this paper allows the analysis of the thermodynamic coupling between compressors and pipes and the off-design performance analysis of the integrated pipeline-compressor system. The introduced simulation approach has been applied to the performance simulation of a typical model pipeline driven by multiple centrifugal compressor pumping stations. It is assumed in the pipeline control schedule that the total pressure at the inlet of compressor stations is kept constant when pipeline operating condition changes. Such pipeline operating conditions include varying ambient temperature and varying natural gas volumetric flow rate. The performance behavior of the pipeline corresponding to the change of operating conditions has been successfully simulated. The introduced pipeline performance simulation approach is generic and can be applied to different pipeline-compressor systems.


Author(s):  
Changduk Kong ◽  
Hongsuk Roh ◽  
Kangtaek Lim

A performance simulation model of the PT6A-62 turboprop engine using the SIMULINK® was proposed to predict transient and steady state behaviors. This SIMULINK has some advantages such as user-friendly circumstance due to the GUI (Graphic User Interfaces) and ease in modification of the computer program. The SIMULINK model consists of subsystems to represent engine gas path components such as flight initial subsystem, compressor subsystem, burner subsystem, compressor turbine subsystem, power turbine, exhaust nozzle subsystem and integrator subsystem. In addition to these subsystems, there are search subsystems to search an appropriate operating point by scaling from the 2-D components look-up table, error matching subsystem to calculate the gas property precisely. In case of steady state validation, performance parameters analyzed by the proposed SIMULINK model were compared with the analysis results by commercial GASTURB program. In the validation of the transient model, the produced dynamic simulation results were compared with analysis results produced by a well-proved computer program using FORTRAN. In performance analysis of the PT6A-62 turboprop engine by the developed SIMULINK model, the steady state simulation was performed at off design points with altitude variation and part throttle, and the transient simulations with step fuel increases for accelerating the engine were carried out from 64% rpm (idle speed) to 94%rpm. In this investigation, the maximum error in all steady state off-design points in part load cases was within 7.33%. In case of transient analysis with different step fuel increases, the acceleration times using the SIMULINK model were well agreed with experimental values, and also the times calculated by the well proven FORTRAN program.


Author(s):  
P. K. Vijayan ◽  
M. Sharma ◽  
D. S. Pilkhwal ◽  
D. Saha ◽  
R. K. Sinha

A one-dimensional theoretical model has been used to analyze the steady state and stability performance of a single-phase, two-phase, and supercritical natural circulation in a uniform diameter rectangular loop. Parametric influences of diameter, inlet temperature, and system pressure on the steady state and stability performance have been studied. In the single-phase liquid filled region, the flow rate is found to increase monotonically with power. On the other hand, the flow rate in two-phase natural circulation systems is found to initially increase, reach a peak, and then decrease with power. For the supercritical region also, the steady state behavior is found to be similar to that of the two-phase region. However, if the heater inlet temperature is beyond the pseudo critical value, then the performance is similar to single-phase loops. Also, the supercritical natural circulation flow rate decreases drastically during this condition. With an increase in loop diameter, the flow rate is found to enhance for all the three regions of operation. Pressure has a significant influence on the flow rate in the two-phase region, marginal effect in the supercritical region, and practically no effect in the single-phase region. With the increase in loop diameter, operation in the single-phase and supercritical regions is found to destabilize, whereas the two-phase loops are found to stabilize. Again, pressure has a significant influence on stability in the two-phase region.


2008 ◽  
Author(s):  
Mikhail P. Strongin

The oscillations of pump performance parameters like head and power corresponding to a wide range of flow-rate values are investigated in the present paper. A centrifugal double suction industrial pump is studied with comparison of test, steady state and averaged transient results. Different turbulence closure models, such as k-ω, and k-ω SST were used. The oscillation behavior of the head and the power of pump is studied for three different pump geometries. The pump model consists of suction, impeller and discharge parts which are meshed and calculated together. This, for instance, naturally permits the effects of non uniformity of velocity distribution on the impeller eye and on the inlet of the discharge segment to be taken into account. The commercial code Fluent 6.3.26 is used for the CFD computations. The results show much better agreement of the test data with averaged transient calculations compared with steady state calculations, especially far away from best efficiency point on the performance curve. Besides, an interesting transient effect, doubling of the frequency of pump parameters oscillations (compared with the blade passing frequency w = n*N) is observed.


Author(s):  
P. K. Vijayan ◽  
D. S. Pilkhwal ◽  
M. Sharma ◽  
D. Saha ◽  
R. K. Sinha

A one dimensional theoretical model has been used to analyze the steady state and stability performance of single-phase, two-phase and supercritical natural circulation in a uniform diameter rectangular loop. Parametric influences of diameter, inlet temperature and system pressure on the steady state and stability performance has been studied. In the single-phase liquid filled region, the flow rate is found to increase monotonically with power. On the other hand the flow rate in two-phase NCS is found to initially increase, reach a peak and then decrease with power. For the supercritical region also, the steady state behaviour is found to be similar to that of two-phase region. However, if the heater inlet temperature is beyond the pseudo critical value, then the performance is similar to single-phase loops. Also, the supercritical natural circulation flow rate decreases drastically during this condition. With increase in loop diameter, the flow rate is found to enhance for all the three regions of operation. Pressure has a significant influence on flow rate in two-phase region marginal effect in supercritical region and practically no effect in the single-phase region. With increase in loop diameter, operation in the single-phase and supercritical regions is found to destabilize whereas the two-phase loops are found to stabilize. Again, pressure has a significant influence on stability in the two-phase region.


Sign in / Sign up

Export Citation Format

Share Document