Parametric study on exergy and NOx metrics of turbofan engine under different design variables

2021 ◽  
pp. 1-26
Author(s):  
Hakan Aygun ◽  
Mohammad Rauf Sheikhi ◽  
Mehmet Kirmizi
Keyword(s):  
Nox Emission ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Turbofan Engine ◽  
Performance And Emission ◽  
Decision Mechanism ◽  
Fuel Flow ◽  
Design Variables

Abstract Examining effects of design variables on performance and emission parameters for gas turbine engines is of high importance. In this study, effects of by-pass ratio (BPR) and turbine inlet temperature (TIT) of turbofan engine on energy, exergy and exhaust emissions are parametrically analyzed at 0.85 Ma and 11 km. Moreover, cruise NOx emission is quantified by Boeing Fuel Flow Method 2 (BFFM2) and DLR methods. As a novelty, Specific NOx Production (SNP) is firstly quantified for PW4000 engine. In this context, parametric cycle equations regarding turbofan engine are encoded so as to compute performance and emission metrics. According to energy analysis, specific fuel consumption (SFC) of the turbofan averagely changes from 19.82 to 18.64 g/ kNs due to rising BPR whereas it increases from 18.62 to 19.93 g/kNs owing to rising TIT.Furthermore, exergy efficiency of turbofan rises from 27.67 % to 29.42 % due to rising BPR whereas it decreases from 29.46 % to 27.65 % owing to rising TIT. As for NOx emission results, the higher BPR leads to the lowering of the SNP index of the turbofan from 0.46 to 0.375 g/kNs while the higher TIT yields to the increase of the SNP index from 0.377 to 0.455 g/kNs. According to the findings of this study, decision mechanism could be improved to find out optimum design variables in terms of eco-friendly aircraft activities.

Practical Implications of Integrating Turbomachinery Into the Air Turborocket

2004 ◽  
Author(s):  
Joshua A. Clough ◽  
Mark J. Lewis
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Launch Vehicle ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Space Launch ◽  
Practical Implications

The development of new reusable space launch vehicle concepts has lead to the need for more advanced engine cycles. Many two-stage vehicle concepts rely on advanced gas turbine engines that can propel the first stage of the launch vehicle from a runway up to Mach 5 or faster. One prospective engine for these vehicles is the Air Turborocket (ATR). The ATR is an innovative aircraft engine flowpath that is intended to extend the operating range of a conventional gas turbine engine. This is done by moving the turbine out of the core engine flow, alleviating the traditional limit on the turbine inlet temperature. This paper presents the analysis of an ATR engine for a reusable space launch vehicle and some of the practical problems that will be encountered in the development of this engine.

scholarly journals Development of 300 kW Class Ceramic Gas Turbine (CGT302)

1995 ◽  
Author(s):  
Kozi Nishio ◽  
Junzo Fujioka ◽  
Tetsuo Tatsumi ◽  
Isashi Takehara
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Pollutant Emissions ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Iso Standard ◽  
Current State ◽  
Ceramic Components

With the aim of achieving higher efficiency, lower pollutant emissions, and multi-fuel capability for small to medium-sized gas turbine engines for use in co-generation systems, a ceramic gas turbine (CGT) research and development program is being promoted by the Japanese Ministry of International Trade and Industry (MITI) as a part of its “New Sunshine Project”. Kawasaki Heavy Industries (KHI) is participating in this program and developing a regenerative two-shaft CGT (CGT302). In 1993, KHI conducted the first test run of an engine with full ceramic components. At present, the CGT302 achieves 28.8% thermal efficiency at a turbine inlet temperature (TIT) of 1117°C under ISO standard conditions and an actual TIT of 1250°C has been confirmed at the rated speed of the basic CGT. This paper consists of the current state of development of the CGT302 and how ceramic components are applied.

Performance Seeking Control of Regenerative Gas Turbine Engines

2000 ◽  
Author(s):  
Nanahisa Sugiyama
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Efficiency Enhancement ◽  
Turbine Inlet Temperature ◽  
Control Variables ◽  
Turbine Engine ◽  
Selection Of ◽  
Engine Life

A Performance Seeking Control (PSC) can realize the operations advantageous enough to accomplish the economy, safety, engine life, and environmental issues by reducing the control margin to the extremity together with selection of the control variables so that various kinds of parameters will be minimized or maximized. This paper describes the results obtained from the simulation study concerning the PSC aiming at the efficiency enhancement, power improvement, and longer engine life of a two-spool regenerative gas turbine engine having two control variables. By constructing the dynamic simulation of the engine, steady-state characteristics and dynamic characteristics are derived; then, a PSC system is designed and evaluated. It is concluded that the PSC for the gas turbine of this type can be realized by the turbine inlet temperature control.

The Application of Ceramics to the Small Gas Turbine

1970 ◽  
Author(s):  
A. F. McLean
Keyword(s):  
Gas Turbine ◽  
Lower Cost ◽  
Ceramic Materials ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Engine Components ◽  
Processing Techniques

This paper reviews the limitations today’s superalloys exercise on the realization of the potential of the gas turbine engine. Ceramic materials are suggested as a means of achieving lower cost and higher turbine inlet temperature in small gas turbine engines. The paper serves to introduce ceramic materials and processing techniques and identifies silicon nitride, silicon carbide and lithium-alumina-silicate as promising materials for high temperature turbine engine components.

scholarly journals An Automated Interactive Design System for Advanced Gas Turbines

1974 ◽  
Author(s):  
K. M. Thomas ◽  
J. J. Piendel
Keyword(s):  
Gas Turbines ◽  
Design System ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Air Cooling ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
The Past ◽  
Engine Design ◽  
Turbine Design

In the past ten years there has been a dramatic increase in turbine inlet temperature in aircraft gas turbine engines. This increase has been made possible by the application of extensive air cooling to turbine parts. The attendent increase in turbine design complexity without an increase in engine design or development time has been made possible by the development of modern computers and computer programs. A computerized turbine automated design system (TADSYS) was developed at Pratt and Whitney Aircraft, which makes extensive use of computer graphics, to meet the needs of modern turbine design.

CFD Analysis and Experimental Validation of the Flow Field in a Rib Roughed Turbine Internal Cooling Channel

2018 ◽  
Vol 0 (0) ◽  
Author(s):  
Yasin Sohret ◽  
T. Hikmet Karakoc
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Internal Cooling ◽  
Gas Turbine Engines ◽  
Cooling Channel ◽  
Turbine Inlet Temperature ◽  
Computational Fluid Dynamics Analysis

Abstract Advances in thermal science force us to develop more efficient systems. The efficiency of widely-used gas turbine engines, is highly dependent on turbine inlet temperature. However, a high turbine inlet temperature yields material deterioration and long term degradation of turbines. To prevent material deterioration, cooling the hot zones of gas turbine engines, particularly turbine components and blades, is a priority. In this way, long term degradation of the turbine is prevented, while the thermal efficiency of the gas turbine engine is boosted. In the current paper, a flow field within a rib roughed blade internal cooling channel is discussed. Within this scope, a computational fluid dynamics analysis is conducted using a Standard k-ω turbulence model. After this, the same case is experimentally investigated. Experimental results obtained from particle image velocimetry measurements are used to validate the results of the computational fluid dynamics analysis. At the end of the study, the flow field is fully mapped with the recirculation and separation zones being clearly pinpointed.

The Effects of Ambient Conditions on Gas Turbine Emissions—Generalized Correction Factors

1978 ◽  
Vol 100 (4) ◽  
pp. 640-646 ◽  
Author(s):  
P. Donovan ◽  
T. Cackette
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Correction Factors ◽  
Oxides Of Nitrogen ◽  
Ambient Conditions ◽  
Nitrogen Emission ◽  
Wide Range

A set of factors which reduces the variability due to ambient conditions of the hydrocarbon, carbon monoxide, and oxides of nitrogen emission indices has been developed. These factors can be used to correct an emission index to reference day ambient conditions. The correction factors, which vary with engine rated pressure ratio for NOx and idle pressure ratio for HC and CO, can be applied to a wide range of current technology gas turbine engines. The factors are a function of only the combustor inlet temperature and ambient humidity.

Thermo-Economic Optimization in the Design of Small-Scale and Residential Cogeneration Systems

2009 ◽  
Author(s):  
C. P. Lea˜o ◽  
S. F. C. F. Teixeira ◽  
A. M. Silva ◽  
M. L. Nunes ◽  
L. A. S. B. Martins
Keyword(s):  
Gas Turbine ◽  
Urban Areas ◽  
Pressure Ratio ◽  
Optimization Method ◽  
Turbine Engines ◽  
Small Scale ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Economic Optimization ◽  
Micro Turbine

In recent years, gas-turbine engines have undergone major improvements both in efficiency and cost reductions. Several inexpensive models are available in the range of 30 to 250 kWe, with electrical efficiencies already approaching 30%, due to the use of a basic air-compressor associated to an internal air pre-heater. Gas-turbine engines offer significant advantages over Diesel or IC engines, particularly when Natural Gas (NG) is used as fuel. With the current market trends toward Distributed Generation (DG) and the increased substitution of boilers by NG-fuelled cogeneration installations for CO2 emissions reduction, small-scale gas turbine units can be the ideal solution for energy systems located in urban areas. A numerical optimization method was applied to a small-scale unit delivering 100 kW of power and 0.86 kg/s of water, heated from 318 to 353K. In this academic study, the unit is based on a micro gas-turbine and includes an internal pre-heater, typical of these low pressure-ratio turbines, and an external heat recovery system. The problem was formulated as a non-linear optimisation model with the minimisation of costs subject to the physical and thermodynamic constraints. Despite difficulties in obtaining data for some of the components cost-equations, the preliminary results indicate that the optimal compressor pressure ratio is about half of the usual values found in large installations, but higher than those of the currently available micro-turbine models, while the turbine inlet temperature remains virtually unchanged.

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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