Performance Cycle Analysis of Turbofan Engine with Interstage Turbine Burner

Abstract

This paper presents the performance-cycle analysis of a dual-spool, separate-exhaust turbofan engine, with an interstage turbine burner (ITB) serving as a secondary combustor. The ITB, which is located at the transition duct between the high-and the low-pressure turbines, is a relatively new concept for increasing specific thrust and lowering pollutant emissions in modern jet engine propulsion. A detailed performance analysis of this engine has been conducted for steady-state engine performance prediction. A code is written and is capable of predicting engine performances (i.e., thrust and thrust specific fuel consumption) at varying flight conditions and throttle settings. Two design-point engines were studied to reveal trends in performance at both full and partial throttle operations. A mission analysis is also presented to ensure the advantage of saving fuel by adding ITB.

Turboprop Cycle Optimization Using Repulsive Particle Swarm Algorithm

“…For a given fuel like JP8, many references give such relations [8]. The components losses and polytropic efficiencies for the basic and advanced technology turboprop correspond to the third and fourth technology level [9], noting that a technology level represents components performance in a 20-year period.…”

Control strategy for turbo-shaft engine with Inter-stage Turbine Burner

“…In general, ITB often serves as a secondary combustor for a gas turbine engine [7][8][9]. The augmented combustion in the turbine will lead to less turbine enthalpy drop during turbine expansion phase.…”

Evaluation of performance properties of two combustor turbofan engine

“…-On the basis of the assumptions, the mass flow of the inlet air into the engine in the function of velocity and flight altitude was determined from the equation (8), and the mass flow of the air inlet into the core engine was determined from the equation (9). The equations (10) and (11) were used to estimate real rotors speed, and then to determine the temperature value of the gases in the inlet section of the high and low pressure turbines. In order to do it a criterion of constant corrected rotation speed of the high pressure turbine rotor was used:…”

“…The results of these works show that such a solution should be more beneficial from the point of view of energy because in a certain part the heating process should be similar to isothermal process which occurs in the cycle of the highest performance -the Carnot cycle [17]. From the ecological point of view, it is shown that practical implementation of the suggested solutions will enable obtainment of maximal temperature of the engine cycle at maintaining unchanged performance, which should have a beneficial influence of limitation of emission of nitrogen oxides [9,10].…”

“…It covers the analysis and energy estimation of the operating cycle of the engine obtained as a result of modifications of the processes taking place in it. Currently, the main streams of modifications of the engine cycle concern additional interstage turbine burning [12,17], or burning in the additional combustor situated between the high and low pressure turbines in a two-spool engine [5,7,9,10]. The results of these works show that such a solution should be more beneficial from the point of view of energy because in a certain part the heating process should be similar to isothermal process which occurs in the cycle of the highest performance -the Carnot cycle [17].…”