scholarly journals High Temperature Combustor Designed for Operation With Coal Derived Low Btu Gaseous Fuels

1980 ◽  
Author(s):  
T. R. Koblish ◽  
L. M. Nucci
Keyword(s):  
Steam Turbine ◽  
Gas Turbine ◽  
Coal Gasification ◽  
Gas Turbine Engine ◽  
Combined Cycle ◽  
Department Of Energy ◽  
Turbine Engine ◽  
Gaseous Fuels ◽  
Coal Gasifier ◽  
Engine Components

Studies sponsored by the U. S. Department of Energy (DOE) have indicated that the combined cycle, incorporating an open cycle gas turbine having a Low Btu gas (LBG) fueled combustor operating at temperatures over 2600 F and a closed cycle steam turbine can produce cost competitive electric power from gasified coal. For increased efficiency, the coal gasification system would be integrated with the gas turbine which supplies the compressed air for the coal gasification system, and the steam turbine which supplies the steam for the gasification system. The coal gasifier would provide a pressurized low heating value (LBG) fuel (at the order of ISO Btu/SCF (5590 kJ/m3) for combustion in the gas turbine engine. Under DOE sponsorship, one of the gas turbine engine components being investigated both analytically and experimentally, is the LBG fueled combustor. This paper describes the LBG configuration background technology utilized in the design of the combustor and the test program outline for substantiation of the design approach.

Flexible manufacturing in repair of gas turbine engine components

1992 ◽  
Author(s):  
KIRK D ◽  
ANDREW VAVRECK ◽  
ERIC LITTLE ◽  
LESLIE JOHNSON ◽  
BRETT SAYLOR
Keyword(s):  
Gas Turbine ◽  
Flexible Manufacturing ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Engine Components

Life assessment of a high temperature probe designed for performance evaluation and health monitoring of an aero gas turbine engine

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Benny George ◽  
Nagalingam Muthuveerappan
Keyword(s):  
Performance Evaluation ◽  
Gas Turbine ◽  
Health Monitoring ◽  
Gas Turbine Engine ◽  
Life Assessment ◽  
Exhaust Gas ◽  
Cycle Fatigue ◽  
Creep Life ◽  
Turbine Engine ◽  
Engine Components

AbstractTemperature probes of different designs were widely used in aero gas turbine engines for measurement of air and gas temperatures at various locations starting from inlet of fan to exhaust gas from the nozzle. Exhaust Gas Temperature (EGT) downstream of low pressure turbine is one of the key parameters in performance evaluation and digital engine control. The paper presents a holistic approach towards life assessment of a high temperature probe housing thermocouple sensors designed to measure EGT in an aero gas turbine engine. Stress and vibration analysis were carried out from mechanical integrity point of view and the same was evaluated in rig and on the engine. Application of 500 g load concept to clear the probe design was evolved. The design showed strength margin of more than 20% in terms of stress and vibratory loads. Coffin Manson criteria, Larsen Miller Parameter (LMP) were used to assess the Low Cycle Fatigue (LCF) and creep life while Goodman criteria was used to assess High Cycle Fatigue (HCF) margin. LCF and HCF are fatigue related damage from high frequency vibrations of engine components and from ground-air-ground engine cycles (zero-max-zero) respectively and both are of critical importance for ensuring structural integrity of engine components. The life estimation showed LCF life of more than 4000 mission reference cycles, infinite HCF life and well above 2000 h of creep life. This work had become an integral part of the health monitoring, performance evaluation as well as control system of the aero gas turbine engine.

Life assessment of a high temperature probe designed for performance evaluation and health monitoring of an aero gas turbine engine

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Benny George ◽  
Nagalingam Muthuveerappan
Keyword(s):  
Performance Evaluation ◽  
Gas Turbine ◽  
Health Monitoring ◽  
Gas Turbine Engine ◽  
Life Assessment ◽  
Exhaust Gas ◽  
Cycle Fatigue ◽  
Creep Life ◽  
Turbine Engine ◽  
Engine Components

Abstract Temperature probes of different designs were widely used in aero gas turbine engines for measurement of air and gas temperatures at various locations starting from inlet of fan to exhaust gas from the nozzle. Exhaust Gas Temperature (EGT) downstream of low pressure turbine is one of the key parameters in performance evaluation and digital engine control. The paper presents a holistic approach towards life assessment of a high temperature probe housing thermocouple sensors designed to measure EGT in an aero gas turbine engine. Stress and vibration analysis were carried out from mechanical integrity point of view and the same was evaluated in rig and on the engine. Application of 500 g load concept to clear the probe design was evolved. The design showed strength margin of more than 20% in terms of stress and vibratory loads. Coffin Manson criteria, Larsen Miller Parameter (LMP) were used to assess the Low Cycle Fatigue (LCF) and creep life while Goodman criteria was used to assess High Cycle Fatigue (HCF) margin. LCF and HCF are fatigue related damage from high frequency vibrations of engine components and from ground-air-ground engine cycles (zero-max-zero) respectively and both are of critical importance for ensuring structural integrity of engine components. The life estimation showed LCF life of more than 4000 mission reference cycles, infinite HCF life and well above 2000 h of creep life. This work had become an integral part of the health monitoring, performance evaluation as well as control system of the aero gas turbine engine.

An Integrated Approach for Gas Turbine Engine Simulation

2000 ◽  
Author(s):  
Zhiwu Xie ◽  
Ming Su ◽  
Shilie Weng
Keyword(s):  
Gas Turbine ◽  
Local Area Network ◽  
Integrated Approach ◽  
Local Area ◽  
Gas Turbine Engine ◽  
Future Research ◽  
Area Network ◽  
Turbine Engine ◽  
Engine Simulation ◽  
Engine Components

Abstract The static and transient performance of a gas turbine engine is determined by both the characteristics of the engine components and their interactions. This paper presents a generalized simulation framework that enables the integration of different component and system simulation codes. The concept of engine simulation integration and its implementation model is described. The model is designed as an object-oriented system, in which various simulation tasks are assigned to individual software components that interact with each other. A new design rationale called “message-based modeling” and its resulting class structure is presented and analyzed. The object model is implemented within a heterogeneous network environment. To demonstrate its flexibility, the codes that deal with different engine components are separately programmed on different computers running various operating systems. These components communicate with each other via a CORBA compliant ORB, which simulates the overall performance of an engine system. The resulting system has been tested on a Local Area Network (LAN) to simulate the transient response of a three-shaft gas turbine engine, subject to small fuel step perturbations. The simulation results for various network configurations are presented. It is evident that in contrast to a standalone computer simulation, the distributed implementation requires much longer simulation time. This difference of simulation efficiency is analyzed and explained. The limitations of this endeavor, along with some future research topics, are also reported in this paper.

The AGT101 Advanced Automotive Gas Turbine

1982 ◽  
Author(s):  
R. A. Rackley ◽  
J. R. Kidwell
Keyword(s):  
United States ◽  
Gas Turbine ◽  
The United States ◽  
Gas Turbine Engine ◽  
Development Project ◽  
Single Stage ◽  
Department Of Energy ◽  
Inlet Temperature ◽  
United States Department ◽  
Turbine Engine

The Garrett/Ford Advanced Gas Turbine Powertrain System Development Project, authorized under NASA Contract DEN3-167, is sponsored by and is part of the United States Department of Energy Gas Turbine Highway Vehicle System Program. Program effort is oriented at providing the United States automotive industry the technology base necessary to produce gas turbine powertrains competitive for automotive applications having: (1) reduced fuel consumption, (2) multi-fuel capability, and (3) low emissions. The AGT101 powertrain is a 74.6 kW (100 hp), regenerated single-shaft gas turbine engine operating at a maximum turbine inlet temperature of 1644 K (2500 °F), coupled to a split differential gearbox and Ford automatic overdrive production transmission. The gas turbine engine has a single-stage centrifugal compressor and a single-stage radial inflow turbine mounted on a common shaft. Maximum rotor speed is 10,472 rad/sec (100,000 rpm). All high-temperature components, including the turbine rotor, are ceramic. AGT101 powertrain development has been initiated, with testing completed on many aerothermodynamic components in dedicated test rigs and start of Mod I, Build 1 engine testing.

Ceramic Composites for Gas Turbine Engines via a New Process

1989 ◽  
Author(s):  
G. H. Schiroky ◽  
A. W. Urquhart ◽  
B. W. Sorenson
Keyword(s):  
Gas Turbine ◽  
Joint Venture ◽  
New Technology ◽  
Ceramic Composites ◽  
Gas Turbine Engine ◽  
Molten Metals ◽  
Oxidation Reactions ◽  
Turbine Engine ◽  
New Process ◽  
Engine Components

A new process for ceramic composites involves the growth of ceramic matrices through shaped preforms using directed oxidation reactions of molten metals. The preforms may consist of reinforcing fibers, whiskers, platelets, or particles, as needed to produce the desired properties in the finished component. This new technology is being developed by Lanxide Corporation and is being applied to gas turbine engine components by Du Pont Lanxide Composites Inc., a joint venture. The paper includes a description of the technology and a discussion of the status of its application to materials for gas turbine engine components.

Design of a Pressurized Fluid Bed Coal Fired Combined Cycle Electric Power Generation Plant

1978 ◽  
Author(s):  
S. Moskowitz ◽  
G. Weth
Keyword(s):  
Electric Power ◽  
Steam Turbine ◽  
Gas Turbine ◽  
Combustion Process ◽  
Combined Cycle ◽  
Department Of Energy ◽  
Process Selection ◽  
Process Technology ◽  
Fluid Bed ◽  
Plant Efficiency

The combination of pressurized fluidized bed (PFB) technology and the gas turbine - steam turbine combined-cycle power system offer a unique opportunity for the production of electric power at increased plant efficiency from the direct combustion of high sulfur coal and that is environmentally acceptable without stack gas cleanup. The concept offers the prospect of earlier commercialization than those systems requiring gasification or liquefication of coal to clean fels. This paper presents the design of a 500-MW commercial powerplant prepared in conjunction with the U.S. Department of Energy sponsored program for the design, construction, and operation of a coal-fired PFB/turbine electric pilot plant. The powerplant approach develops over 60 percent of the plant capacity by multiple gas turbine gas turbine-generators and the balance of the capacity by a steam turbine-generator. The paper describes the fluid bed process selection of an air heater cycle. With two-thirds of the compressor discharge air indirectly heated within an in-bed gas-to-air heat exchanger and one-third of the compressor air involved in the combustion process, technology requirements for hot gas cleanup and turbine protection are minimized. This approach, which offers a coal-pile-to-busbar plant efficiency of over 40 percent is superior to other concepts and contemporary plants in terms of plant arrangement flexibility, part-load performance, power availability, and provides a low risk in development toward commercialization in the 1980’s.

Experimental and Numerical Correlation of Impact of Spherical Projectile for Damage Analysis of Aero Engine Component

2016 ◽  
Vol 66 (2) ◽  
pp. 193 ◽  
Author(s):  
Anuradha Nayak Majila ◽  
Rajeev Jain ◽  
Chandru Fernando D. ◽  
S. Ramachandra
Keyword(s):  
Finite Element ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Metallographic Analysis ◽  
Damage Analysis ◽  
Alloy Plate ◽  
Turbine Engine ◽  
Aero Engine ◽  
Engine Components ◽  
The Impact

<p>Studies the impact response of flat Titanium alloy plate against spherical projectile for damage analysis of aero engine components using experimental and finite element techniques. Compressed gas gun has been used to impart speed to spherical projectile at various impact velocities for damage studies. Crater dimensions (diameter and depth) obtained due to impact have been compared with finite element results using commercially available explicit finite element method code LS-DYNA. Strain hardening, high strain rate and thermal softening effect along with damage parameters have been considered using modified Johnson-Cook material model of LS-DYNA. Metallographic analysis has been performed on the indented specimen. This analysis is useful to study failure analysis of gas turbine engine components subjected to domestic object damage of gas turbine engine. </p><p> </p>

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