Analysis of Indirectly Fired Gas Turbine for Wet Biomass Fuels Based on Commercial Micro Gas Turbine Data

2002 ◽  
Author(s):  
Brian Elmegaard ◽  
Bjo̸rn Qvale
Keyword(s):  
Gas Turbine ◽  
Process Integration ◽  
The Novel ◽  
Environmental Friendliness ◽  
Waste Products ◽  
Pressure Losses ◽  
Micro Gas Turbine ◽  
Typical Data ◽  
Wet Biomass ◽  
Simple Change

The results of a study of a novel gas turbine configuration is being presented. In this power plant, an Indirectly Fired Gas Turbine (IFGT), is being fueled with very wet biomass. The exhaust gas is being used to dry the biomass, but instead of striving to recover as much as possible of the thermal energy, which has been the practice up to now, the low temperature exhaust gases after having served as drying agent, are lead out into the environment; a simple change of process integration that has a profound effect on the performance. Four different cycles have been studied. These are the Simple IFGT fueled by dry biomass assuming negligible pressure loss in the heat exchanger and the combustion chamber, the IFGT fueled with wet biomass (Wet IFGT) assuming no pressure losses, and finally both the Simple and the Wet IFGT incorporating typical data for pressure losses of commercially available micro turbines. The study shows that the novel configuration, in which an IFGT and a drying unit have been combined, has considerable merit, in that its performance exceeds that of the currently available methods converting wet biomass to electric power by a factor of five. The configuration also has clear advantages with respect to corrosion and to the environmental friendliness and the quantity of the waste products and their usefulness.

A Study on the Flowfield of an Innovative Z-Flowpath Gas Turbine Combustor

2010 ◽  
Author(s):  
Zongming Yu ◽  
Yong Huang ◽  
Fang Wang
Keyword(s):  
Gas Turbine ◽  
Reverse Flow ◽  
Flow Path ◽  
Main Flow ◽  
Wall Area ◽  
Pressure Losses ◽  
Micro Gas Turbine ◽  
Primary Zone ◽  
Commercial Code ◽  
The Stability

Reverse flow combustors were widely used in small and micro gas turbine engines. The wall area of this type of combustors was quite large. And there were two flow turning points in their flow-path. Thus the wall cooling and main flow dilution were two intrinsic problems for them. Apart from that, their high pressure losses and heavy weight were also two problems which seriously deteriorate the performance of the engines. Moreover, their primary hole jets on opposite walls were non-symmetrical, which would affect the stability and intensity of the recirculation flows. In order to improve the combustion performance, a new conceptual Z-flowpath combustor was proposed. The new combustor consisted of two 45 degree yawing instead of returning in the main flow-path. The flowfield of the new combustor was predicted by the commercial code FLUENT, after a validation for the flowfield in a model reverse flow combustor with previous experimental results. The prediction showed that the flowfield of the primary zone in the Z-flowpath combustor was highly symmetrical, the size and the intensity of the recirculation zone were about 10 and 2 times greater than the normal reverse flow combustor, respectively, while the pressure loss and the total area of the flame tube wall of the Z-flowpath combustor were decreased dramatically to be 69.4% and 51% of that in the reverse flow combustor, respectively.

scholarly journals Shock Waves Analysis of the Novel Intake Design Sytem for a Scramjet Propulsion

2021 ◽  
Vol 20 ◽  
pp. 67-75
Author(s):  
Abdulla Khamis Alhassani ◽  
Mohanad Tarek Mohamed ◽  
Mohammed Fares ◽  
Sharul Sham Dol
Keyword(s):  
Shock Waves ◽  
Gas Turbine ◽  
Aerospace Industry ◽  
Supersonic Combustion ◽  
The Novel ◽  
Turbine Engine ◽  
Pressure Losses ◽  
Air Stream ◽  
Compression Mechanism ◽  
Novel Design

The supersonic combustion scramjet in the inlet applies the shock waves compression mechanism tosubstitute the actual compressor from a gas turbine engine. The scramjet works with combustion of fuel throughthe air stream in supersonic condition at least with Mach 5. Novel design of a scramjet intake system was madewith variations in the angle of the fins and entrance width. The best combination of diameter and inclinationangle was 1.75 m and 15 degrees, respectively. The findings were able to increase the oblique shock waveinteractions and supplicate effective combustion and reduce pressure losses for the effective application ofscramjet system, which can be significant for aerospace industry.

Parametric Analysis on a Novel Hybrid System of Solid Oxide Fuel Cell and Micro Gas Turbine

2010 ◽  
Author(s):  
Wenshu Zhang ◽  
Huisheng Zhang ◽  
Shilie Weng
Keyword(s):  
Fuel Cell ◽  
Solid Oxide Fuel Cell ◽  
Gas Turbine ◽  
Hybrid System ◽  
Parametric Analysis ◽  
Solid Oxide ◽  
Methane Reforming ◽  
The Novel ◽  
Oxide Fuel ◽  
Micro Gas Turbine

This paper presents the steady state parametric analysis of the solid oxide fuel cell and micro gas turbine hybrid system based on the IPSEpro software. The characteristic of the novel hybrid system is that both the fuel entering the heat exchanger reformer (HER) and air entering the fuel cell are preheated by mixing with the anode exhaust and cathode exhaust respectively, and thus the normally used heat exchangers can be cut. The heat exchange reformer is introduced for methane reforming. The analysis of the effects of methane reforming degree and the fuel utilization on the hybrid system performance is performed. The efficiency of the hybrid system is up to 67.3% at the design point. The results show the novel hybrid system has great potential for the practical application.

Effects of Air Induct Structure to Flow Uniformity and Resistance for Primary Surface Recuperator of a Micro Gas Turbine

2010 ◽  
Author(s):  
Wei Qu ◽  
Shan Gao
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Loss ◽  
Air Flow ◽  
Flow Distribution ◽  
Structure Design ◽  
Flow Uniformity ◽  
Local Pressure ◽  
Pressure Losses ◽  
Micro Gas Turbine

Primary surface recuperator is important for micro gas turbines, the flow distribution and pressure loss are sensitive to the induct structure design significantly. The air induct structure for one recuperator is modelled and simulated. Several flow fields and pressure losses are obtained for different designs of air induct structure. The air induct structure can affect the flow uniformity, further influence the pressure loss a lot. For several changes of air induct structure, the non-distribution of air flow can be decreased from 67% to 13%, and the pressure loss can be decreased to 50% of the original. Considering the recuperator design and the gas turbine, one optimized structure is recommended, which has less local pressure loss and better flow distribution.

Experimental Investigations of Pressure Losses on the Performance of a Micro Gas Turbine System

2010 ◽  
Author(s):  
Jan Zanger ◽  
Axel Widenhorn ◽  
Manfred Aigner
Keyword(s):  
Steady State ◽  
Electric Power ◽  
Gas Turbine ◽  
Pressure Loss ◽  
System Stability ◽  
Pressure Losses ◽  
Micro Gas Turbine ◽  
Additional Pressure ◽  
Surge Margin ◽  
Compressor Surge

Pressure losses between compressor outlet and turbine inlet are a major issue of overall efficiency and system stability for a SOFC/MGT hybrid power plant system. The goal of this work is the detailed analysis of the effects of additional pressure losses on MGT performance in terms of steady-state and transient conditions. The experiments were performed at the micro gas turbine test rig at the German Aerospace Centre in Stuttgart using a butterfly control valve to apply additional pressure loss. The paper reports electric power and pressure characteristics at steady-state conditions, as well as, a new surge limit, which was found for the Turbec T100 micro gas turbine. Furthermore, the effects of additional pressure loss on compressor surge margin are quantified and a linear relation between relative surge margin and additional pressure loss is shown. For transient variation of pressure loss at constant turbine speed time delays are presented and a compensation issue of the commercial gas turbine controller is discussed. Finally, bleed-air blow-off and reduction of turbine outlet temperature are introduced as methods of increasing surge margin. It is quantified that both methods have a substantial effect on compressor surge margin. Furthermore, a comparison between both methods is given in terms of electric power output.

Experimental Investigation of an Inverted Brayton Cycle Micro Gas Turbine for CHP Application

2017 ◽  
Author(s):  
Eleni Agelidou ◽  
Thomas Monz ◽  
Andreas Huber ◽  
Manfred Aigner
Keyword(s):  
Gas Turbine ◽  
Electrical Power ◽  
Primary Energy ◽  
Pollutant Emissions ◽  
Stable Operation ◽  
Brayton Cycle ◽  
Single Family ◽  
Gas Treatment ◽  
Pressure Losses ◽  
Micro Gas Turbine

Decentralized heat and power (CHP) production constitutes a promising solution to reduce the primary energy consumption and greenhouse gas emissions. Here, micro gas turbine (MGT) based CHP systems are particularly suitable due to their low pollutant emissions without exhaust gas treatment. Typically, the electrical power demand for single houses ranges from 1 to several kWel. However, downsizing turbocharger components of a conventional MGT CHP system can reduce electrical efficiencies since losses like seal and tip leakages, generally do not scale proportionally with size. By introducing an inverted Brayton Cycle (IBC) based MGT this potential can be exploited. The IBC keeps the volumetric flows constant while mass flow and thermodynamic work are scaled by the ratio of pressure level. Since the performance of turbocharger components is mainly driven by the volumetric flow they should be applicable for both cycles. Hence, smaller power outputs can be achieved. The overall aim of this work, is the development of a recuperated inverted MGT CHP unit for a single family house with 1 kWel. This paper presents an experimental study of the applicability and feasibility of a conventional MGT operated in IBC mode. The demonstrator was based on a single shaft, single stage conventional MGT. Reliable start up and stable operation within the entire operating range from 180 000 rpm to 240 000 rpm are demonstrated. The turbine outlet pressure varied between 0,5 bar (part load) and 0,3 bar absolute (full load). All relevant parameters such as pressure losses and efficiencies of the main components are investigated. Moreover, the power output and the mechanical and thermal losses were analyzed in detail. Although the results indicated that the mechanical and heat losses have a high influence on the performance and economic efficiency of the system, the prototype shows great potential for further development.

A Novel Approach to the Stabilization of Auto-Igniting Flames Within a Gas Turbine Sequential Combustor, Through the Control of Static Temperature Variation Along the Premixing and Flame Zones

2020 ◽  
Author(s):  
K. J. Syed ◽  
A. C. Benim ◽  
E. Pasqualotto ◽  
R. C. Payne
Keyword(s):  
Gas Turbine ◽  
Pressure Loss ◽  
The Novel ◽  
Turbine Stage ◽  
Critical Aspect ◽  
Single Digit ◽  
Pressure Losses ◽  
Hot Gas ◽  
Novel Approach ◽  
Novel Concept

Abstract The present work proposes a novel concept for a sequential burner and combustor that can be located downstream of a first stage combustor or downstream of a turbine stage in the case of a reheat gas turbine. The novel aspect is the method of flame anchoring, which, instead of relying on dump expansion as in the present state-of-the-art, relies on setting up a static temperature gradient through the premixing and flame zones. The advantage of this is that anchoring of the auto-igniting flame is not dependent on fluid mechanic phenomena, and reaction can proceed at rates governed by the chemical kinetics. Under these circumstances, CO can reach its equilibrium in ≪ 1ms, which allows for compactness and the potential of single digit NOx emissions at hot gas temperatures in excess of 2100K. Pressure loss is a critical aspect, as the concept requires flows to be accelerated to high velocities (M∼0.7). However, it is shown that pressure losses can be limited to 4–5%. The concept is evaluated through analytical and 1D approaches, while the feasibility of achieving a design that meets the desired turbulence characteristics at an acceptable pressure loss is demonstrated by way of 3D CFD.

Experimental Investigations of Pressure Losses on the Performance of a Micro Gas Turbine System

2011 ◽  
Vol 133 (8) ◽  
Author(s):  
Jan Zanger ◽  
Axel Widenhorn ◽  
Manfred Aigner
Keyword(s):  
Steady State ◽  
Electric Power ◽  
Gas Turbine ◽  
Pressure Loss ◽  
Test Rig ◽  
Pressure Losses ◽  
Micro Gas Turbine ◽  
Additional Pressure ◽  
Surge Margin ◽  
Compressor Surge

Pressure losses between the compressor outlet and the turbine inlet are a major issue of overall efficiency and system stability for a solid oxide fuel cell/micro gas turbine (MGT) hybrid power plant system. The goal of this work is the detailed analysis of the effects of additional pressure losses on MGT performance in terms of steady-state and transient conditions. The experiments were performed using the micro gas turbine test rig at the German Aerospace Centre in Stuttgart using a butterfly control valve to apply additional pressure loss. This paper reports electric power and pressure characteristics at steady-state conditions as well as a new surge limit for this Turbec T100 micro gas turbine test rig. Furthermore, the effects of additional pressure loss on the compressor surge margin are quantified and a linear relation between the relative surge margin and additional pressure loss is shown. For transient variation of pressure loss at constant turbine speed, time delays are presented and an instability issue of the commercial gas turbine controller is discussed. Finally, bleed-air blow-off and reduction of the turbine outlet temperature are introduced as methods of increasing the surge margin. It is quantified that both methods have a substantial effect on the compressor surge margin. Furthermore, a comparison between both methods is given in terms of electric power output.

Sign in / Sign up

Export Citation Format

Share Document