Thermodynamic Performance Prediction of Air-Film Blade Cooled Gas Turbine Based Cogeneration Cycle for Marine Propulsion Applications

2018 ◽  
Author(s):  
Shivam Mishra ◽  
Sanjay R
Keyword(s):  
Gas Turbine ◽  
Performance Prediction ◽  
Marine Propulsion ◽  
Thermodynamic Performance ◽  
Air Film ◽  
Cogeneration Cycle

Performance Characteristics of Indirect-Fired Gas Turbine/Cogeneration Cycles

1982 ◽  
Author(s):  
J. C. Lee
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Inlet Temperature ◽  
Closed Cycle ◽  
Design Point ◽  
Partial Load ◽  
Thermodynamic Performance ◽  
Cogeneration System ◽  
Open Cycle ◽  
Cogeneration Cycle

General characteristics equations for cogeneration cycle thermodynamic performance were derived and expressed as functions of the power-to-heat ratio. Based on these equations, design point performance of indirect-fired open-cycle and closed-cycle gas turbine/cogeneration systems were analyzed and compared with those of steam turbine/cogeneration system. Effects of gas turbine pressure ratio and inlet temperature on design point performance were evaluated. Off-design partial load performances of the three cogeneration systems using various control modes were also investigated. Results indicated significant efficiency advantage of the closed-cycle gas turbine/cogeneration system over the others for both design and off-design operations.

Thermal performance prediction of a solar hybrid gas turbine

Solar Energy ◽  
2012 ◽  
Vol 86 (7) ◽  
pp. 2116-2127 ◽  
Author(s):  
G. Barigozzi ◽  
G. Bonetti ◽  
G. Franchini ◽  
A. Perdichizzi ◽  
S. Ravelli
Keyword(s):  
Gas Turbine ◽  
Thermal Performance ◽  
Performance Prediction

The Combustion Gas Turbine: Its History, Development, and Prospects

1939 ◽  
Vol 141 (1) ◽  
pp. 197-222 ◽  
Author(s):  
Adolf Meyer
Keyword(s):  
Gas Turbine ◽  
Power Supply ◽  
Chemical Processes ◽  
Wind Tunnels ◽  
Inlet Temperature ◽  
Reciprocating Motion ◽  
Combustion Gas ◽  
Marine Propulsion ◽  
Cracking Process ◽  
Principal Advantage

By “combustion gas turbine” is meant a turbine actuated by the steady flow of the products of a continuous combustion under pressure in a combustion chamber. Inventors appear to have been at work on the gas turbine since 1791, the original attractions of the proposal being its simplicity and the elimination of the reciprocating motion of the early steam engines. Simplicity remains the principal advantage of the gas turbine, though the first applications have been made possible by the needs of special chemical processes, such as the Houdry cracking process. The efficiency attainable under present conditions is 17–18 per cent, but this would be increased to 23 per cent if the gas inlet temperature could be raised from 1,000 to 1,300 deg. F. The proposed new fields of application of the gas turbine include locomotive and marine propulsion, blast furnace plants, and the power supply for wind tunnels.

Modelling the Air-Cooled Gas Turbine: Part 1 — General Thermodynamics

2001 ◽  
Author(s):  
J. B. Young ◽  
R. C. Wilcock
Keyword(s):  
Gas Turbine ◽  
Performance Prediction ◽  
Real Gas ◽  
Thermal Mixing ◽  
Ideal Gases ◽  
Formal Framework ◽  
Considerable Simplification ◽  
Cycle Efficiency ◽  
General Thermodynamics

This paper is Part I of a study concerned with developing a formal framework for modelling air-cooled gas turbine cycles and deals with basic thermodynamic issues. Such cycles involve gas mixtures with varying composition which must be modelled realistically. A possible approach is to define just two components, air and gas, the latter being the products of stoichiometric combustion of the fuel with air. If these components can be represented as ideal gases, the entropy increase due to compositional mixing, although a true exergy loss, can be ignored for the purpose of performance prediction. This provides considerable simplification. Consideration of three idealised simple cycles shows that the introduction of cooling with an associated thermal mixing loss does not necessarily result in a loss of cycle efficiency. This is no longer true when real gas properties and turbomachinery losses are included. The analysis clarifies the role of the cooling losses and shows the importance of assessing performance in the context of the complete cycle. There is a strong case for representing the cooling losses in terms of irreversible entropy production as this provides a formalised framework, clarifies the modelling difficulties and aids physical interpretation. Results are presented which show the effects on performance of varying cooling flowrates and cooling losses. A comparison between simple and reheat cycles highlights the rôle of the thermal mixing loss. Detailed modelling of the heat transfer and cooling losses is discussed in Part II of this paper.

scholarly journals Metamodels of a gas turbine powered marine propulsion system for simulation and diagnostic purposes

2015 ◽  
Vol 12 (1) ◽  
pp. 1-14 ◽  
Author(s):  
U. Campora ◽  
M. Capelli ◽  
C. Cravero ◽  
R. Zaccone
Keyword(s):  
Gas Turbine ◽  
Response Surfaces ◽  
Propulsion System ◽  
Direct Simulation ◽  
Analysis Method ◽  
Simulation Code ◽  
Marine Propulsion ◽  
Performance Reduction ◽  
Input Variables ◽  
Marine Propulsion System

The paper presents the application of artificial neural network for simulation and diagnostic purposes applied to a gas turbine powered marine propulsion plant. A simulation code for the propulsion system, developed by the authors, has been extended to take into account components degradation or malfunctioning with the addition of performance reduction coefficients. The above coefficients become input variables to the analysis method and define the system status at a given operating point. The simulator is used to generate databases needed to perform a variable selection analysis and to tune response surfaces for both direct (simulation) and inverse (diagnostic) purposes. The application of the methodology to the propulsion system of an existing frigate version demonstrate the potential of the approach.

Thermodynamic Performance of Complex Gas Turbine Cycles

2002 ◽  
Author(s):  
Sanjay ◽  
Onkar Singh ◽  
B. N. Prasad
Keyword(s):  
Gas Turbine ◽  
Specific Power ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Air Cooling ◽  
Gas Turbine Engines ◽  
Current State ◽  
Thermodynamic Performance ◽  
Internal Convection ◽  
Plant Efficiency

This paper deals with the thermodynamic performance of complex gas turbine cycles involving inter-cooling, re-heating and regeneration. The performance has been evaluated based on the mathematical modeling of various elements of gas turbine for the real situation. The fuel selected happens to be natural gas and the internal convection / film / transpiration air cooling of turbine bladings have been assumed. The analysis has been applied to the current state-of-the-art gas turbine technology and cycle parameters in four classes: Large industrial, Medium industrial, Aero-derivative and Small industrial. The results conform with the performance of actual gas turbine engines. It has been observed that the plant efficiency is higher at lower inter-cooling (surface), reheating and regeneration yields much higher efficiency and specific power as compared to simple cycle. There exists an optimum overall compression ratio and turbine inlet temperature in all types of complex configuration. The advanced turbine blade materials and coating withstand high blade temperature, yields higher efficiency as compared to lower blade temperature materials.

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