Transient Analysis of Gas Turbine Power Plants, Using the Huntorf Compressed Air Storage Plant as an Example

Journal of Propulsion and Power

Lippke

1994

A new computational method for accurate simulation of the nonlinear, dynamic behavior of single-and multispool core engines, turbofan engines, and power-generation gas turbine engines is presented in Part I of this article. In order to perform the simulation, a modularly structured computer code has been developed that includes individual mathematical modules representing various engine components. The generic structure of the code enables the simulation of arbitrary engine configurations ranging from single-spool thrust generation to multispool thrust/power generation engines under adverse dynamic operating conditions. For precise simulation of turbine and compressor components, row-by-row calculation procedures were implemented that account for the specific turbine and compressor cascade and blade geometry and characteristics. Nomenclaturespecific heat capacities C w = specific heat capacity of the wall D h = hydraulic diameter /z, H = static, total enthalpy / = second moment of inertia of shaft K = kinetic energy per unit mass L = stage mechanical energy, length / = specific mechanical energy ra = mass flow p, P = static, total pressure Q = rate of heat flow R = gas constant S = cross-sectional area 7, 7* = static, total temperature T = stress tensor, e/e,T, 7 t = time V = volume V = absolute velocity vector a = heat transfer coefficient e = convergence tolerance K = ratio of specific heats IJL ~ mass flow ratio, absolute viscosity p = density a) = angular velocity Subscripts A = air C = convection CA = air side convection CG = gas side convection c = cold F = fuel Fi -film G = combustion gas h = hot

Section: Engine Simulation Backgroundmentioning

confidence: 99%

Nonlinear dynamic simulation of single- and multispool core engines. I - Computational method. II - Simulation, code validation

Journal of Propulsion and Power

Lippke

1994

“…To estimate gas turbine starting characteristics, Agrawal and Yunis (1982) generated a set of steady component characteristics, where the turbine and compressor components are represented by overall steady performance maps. Engine representation by performance maps, as briefly addressed above, and comprehensively discussed by Schobeiri (1985a,b,c) and Schobeiri and Haselbacher (1985), exhibits a useful tool for approximating engine behavior within the operation range dictated by the component maps. However, the detailed information that is crucial for engine development and design cannot be provided at this simulation level.…”

Section: Engine Simulation Backgroundmentioning

confidence: 99%

Advances in Nonlinear Dynamic Engine Simulation With an Example: Dynamic Performance Behavior of a Gas Turbine With One Reheat Turbine Stage and Two Combustion Chambers

Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation;

1996

The paper discusses some recent advances in dynamic engine simulation technology. A brief presentation of the physical background is followed by a detailed description of the turbine component, its modular representation, and its integration into the nonlinear dynamic engine simulation code GETRAN. In order to ensure the capability, accuracy, robustness, and reliability of the turbine module in interaction with GETRAN, comprehensive critical performance assessment and validation tests were performed. Two conceptually different engine configurations were dynamically simulated and their transient behavior was analyzed and compared with each other. As the first example, a full scale dynamic simulation of an advanced high performance single spool single shaft power generation gas turbine engine is presented. The second example includes the full scale dynamic simulation of an advanced power generation gas turbine engine with a reheat turbine stage and two combustion chambers. The comparison of these engines shows clearly the impact of the dynamic operation on the performance of individual gas turbine engines under consideration.

“…In order to address these issues, Schobeiri (1985aSchobeiri ( ,b,c, 1986Schobeiri ( , 1987a and Schobeiri and Haselbacher (1985) developed the modularly structured computer code COTRAN for simulating the nonlinear dynamic behavior of single-shaft power generation gas turbine engines. To account for the heat exchange between the material and the working fluid during a transient event, diabatic processes are employed in COTRAN.…”

Section: Engine Representationsmentioning

confidence: 99%

“…In this paper, the design concept, the theoretical background for the development of GETRAN, and several simulation cases are presented. Schobeiri and Haselbacher (1985) and Schobeiri (1986Schobeiri ( ,1987b. Although COTRAN represents an advanced, nonlinear dynamic code, its simulation capability is restricted to singleshaft power generation gas turbine engines and, thus, cannot be used for simulating multispool aircraft engines.…”

Section: Introductionmentioning

confidence: 99%

“…Consequently, the response of the real system to the intervention of the controller cannot be verified. These and other parameters are required inputs to the controller for triggering precautionary actions such as active surge control, achieved by adjusting variable compressor stator blades.In order to address these issues, Schobeiri (1985aSchobeiri ( ,b,c, 1986Schobeiri ( , 1987a and Schobeiri and Haselbacher (1985) developed the modularly structured computer code COTRAN for simulating the nonlinear dynamic behavior of single-shaft power generation gas turbine engines. To account for the heat exchange between the material and the working fluid during a transient event, diabatic processes are employed in COTRAN.…”

mentioning

confidence: 99%

See 1 more Smart Citation

GETRAN: A Generic, Modularly Structured Computer Code for Simulation of Dynamic Behavior of Aero- and Power Generation Gas Turbine Engines

Journal of Engineering for Gas Turbines and Power

Lippke

1994

The design concept, the theoretical background essential for the development of the modularly structured simulation code GETRAN, and several critical simulation cases are presented in this paper. The code being developed under contract with NASA Lewis Research Center is capable of simulating the nonlinear dynamic behavior of single-and multispool core engines, turbofan engines, and power generation gas turbine engines under adverse dynamic operating conditions. The modules implemented into GETRAN correspond to components of existing and new-generation aero-and stationary gas turbine engines with arbitrary configuration and arrangement. For precise simulation of turbine and compressor components, row-by-row diabatic and adiabatic calculation procedures are implemented that account for the specific turbine and compressor cascade, blade geometry, and characteristics. The nonlinear, dynamic behavior of the subject engine is calculated solving a number of systems of partial differential equations, which describe the unsteady behavior of each component individually. To identify each differential equation system unambiguously, special attention is paid to the addressing of each component. The code is capable of executing the simulation procedure at four levels, which increase with the degree of complexity of the system and dynamic event. As representative simulations, four different transient cases with single-and multispool thrust and power generation engines were simulated. These transient cases vary from throttling the exit nozzle area, operation with fuel schedule, rotor speed control, to rotating stall and surge. Downloaded From: http://gasturbinespower.asmedigitalcollection.asme.org/ on 09/20/2013 Terms of Use: http://asme.org/terms Engine RepresentationsStudies of the dynamic behavior of aircraft engines were conducted earlier by NASA Lewis Research Center using the component performance map representation for simulating engines. Koenig and Fishbach (1972) and Seldner et al. (1972) utilized overall component performance maps in their simulation program GENENG, which performs purely steady-state computations. In order to account for the system dynamics, Seller and Daniele (1975) extended the code by introducing simplified dynamic equations: A similar technique was also applied by Fawke and Saravanamuttoo (1972). In a report about a hybrid simulation of single-and twin-spool turbofan engines, Szuch (1974) also described the representation of the engine components by overall performance maps. To estimate gas turbine starting characteristics, Agrawal and Yunis (1982) generated a set of steady component characteristics, where the turbine and compressor components are represented by overall steady performance maps. The engine representation by performance maps, as briefly addressed above and comprehensively discussed by Schobeiri (1985a), exhibits a useful tool for approximating engine behavior within the operation range defined by the component maps. However, the detailed information that is crucial for engine develop...