scholarly journals Design Analysis of the General Electric T58 Engine

1958 ◽  
Author(s):  
F. W. Hegland
Keyword(s):  
Gas Turbine ◽  
Design Analysis ◽  
General Electric

The General Electric T58 is a lightweight, compact 1050 HP shaft powered gas turbine designed primarily for helicopters. Under sponsorship of the Navy Bureau of Aeronautics, this design was initiated with a development contract in June 1953.

Virtual Gas Turbines Part II: an Automated Whole-Engine Secondary Air System Model Generation

2021 ◽  
Author(s):  
Davendu Y. Kulkarni ◽  
Luca di Mare
Keyword(s):  
Gas Turbine ◽  
Network Model ◽  
Design Analysis ◽  
Model Generation ◽  
Time Cost ◽  
Flow Network ◽  
Turbine Engine ◽  
Geometry Model ◽  
Air System ◽  
Secondary Air

Abstract The design and analysis of the secondary air system (SAS) of gas turbine engine is a complex and time-consuming process because of its complicated geometry topology. The conventional SAS design-analysis model generation process is quite tedious, time consuming. It is still heavily dependent on human expertise and thus incurs high time-cost. This paper presents an automated, whole-engine SAS flow network model generation methodology. During the SAS preprocessing step, the method accesses a pre-built whole-engine geometry model created using a novel, in-house, feature-based geometry modelling environment. It then transforms the engine geometry features into the features suitable for SAS flow network analysis. The proposed method not only extracts the geometric information from the computational geometry but also retrieves additional non-geometric attributes such as, rotational frames, boundary types, materials and boundary conditions etc. Apart from ensuring geometric consistency, this methodology also establishes a bi-directional information exchange protocol between engine geometry model and SAS flow network model, which enables making engine geometry modifications based on SAS analysis results. The application of this feature mapping methodology is demonstrated by generating the secondary air system (SAS) flow network model of a modern three-shaft gas turbine engine. This capability is particularly useful for the integration of geometry modeler with the simulation framework. The present SAS model is generated within a few minutes, without any human intervention, which significantly reduces the SAS design-analysis time-cost. The proposed method allows performing a large number of whole-engine SAS simulations, design optimisations and fast re-design activities.

Development, Fabrication, and Testing of a Prototype Water-Cooled Gas Turbine Nozzle

1983 ◽  
Vol 105 (1) ◽  
pp. 114-119 ◽  
Author(s):  
M. F. Collins ◽  
M. C. Muth ◽  
W. F. Schilling
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Small Scale ◽  
General Electric ◽  
Process Technology ◽  
Aqueous Corrosion ◽  
Post Test ◽  
Efficient Heat Transfer ◽  
Gas Turbine Nozzle ◽  
Industrial Gas Turbine

The design and development of a water-cooled high temperature gas turbine has been under active investigation by the General Electric Gas Turbine Division for the past 15 years. The transition from testing small scale, laboratory-size experimental hardware to full scale industrial gas turbine components was initiated in 1975 by General Electric and extended further under the U.S. Department of Energy’s High Temperature Turbine Technology (HTTT) program. A key element in this transition was the identification of a composite (hybrid) design for the first stage nozzles. This design permits efficient heat transfer to the water-cooling passageways, thus lowering effective strains and increasing part life. This paper describes the metallurgical considerations and process technology required for such hardware. A review of the materials selection criteria utilized for the nozzle is presented, along with the results of several materials development programs aimed at determining metallurgical compatibility of the component materials, diffusion bonding behavior and both hot corrosion and aqueous corrosion performance of key materials. A brief description of the actual cascade testing of the part is given, along with results of a post-test metallurgical analysis of the tested hardware.

Turbine-Compressor Train Uprated for 30% Increase in Gas Flow

1991 ◽  
Author(s):  
C. D. (Charlton) Breon ◽  
D. R. (Daniel) Veth
Keyword(s):  
High Pressure ◽  
Natural Gas ◽  
Gas Turbine ◽  
Centrifugal Compressor ◽  
Gas Flow ◽  
Gas Injection ◽  
Oil Field ◽  
General Electric ◽  
Prudhoe Bay

A turbine-compressor train consisting of a General Electric MS5001 Model R single-shaft gas turbine, a Philadelphia Gear speed-increasing gearbox, and a Dresser-Clark centrifugal compressor was uprated for 30% increased gas throughput. This train is one of thirteen units operated by ARCO Alaska, Inc. for high pressure natural gas injection service in Alaska’s Prudhoe Bay Oil Field. The uprate included an in-place conversion of the gas turbine from a Model R to a Model P configuration. This paper describes the engineering, planning, and implementation activities that led up to the successful uprate of this train with only a 24 day equipment outage.

Optimization Concerns for Combined Cycle Power Plants: II — Optimum Fuel Gas Heating

2003 ◽  
Author(s):  
Walter I. Serbetci
Keyword(s):  
Gas Turbine ◽  
Power Output ◽  
Heat Rate ◽  
Combined Cycle ◽  
Hot Water ◽  
Fuel Temperature ◽  
General Electric ◽  
Fuel Gas ◽  
Gas Heating ◽  
Overall Efficiency

As the second study in a sequence of studies conducted on the optimization of combined cycle plants [Ref. 1], this paper presents the effects of fuel gas heating on plant performance and plant economics for various 1×1×1 configurations. First, the theoretical background is presented to explain the effects of fuel gas heating on combustion turbine efficiency and on the overall efficiency of the combined cycle plant. Then, *CycleDeck-Performance Estimator™ and *GateCycle™ computer codes were used to investigate the impact of fuel gas heating on various 1×1×1 configurations. The configurations studied here are: 1) GE CC107FA with three pressure/reheat HRSG and General Electric PG7241(FA) gas turbine (Fig. 1), 2) GE CC106FA with three pressure/reheat HRSG and General Electric PG6101(FA) gas turbine and, 3) GE CC 107EA with three pressure/non-reheat HRSG with General Electric PG7121(EA) gas turbine. In all calculations, natural gas with high methane percentage is used as a typical fuel gas. Hot water from the outlet of IP economizer is used to heat the fuel gas from its supply temperature of 80 °F (27 °C). Heating the fuel gas to target temperatures of 150 °F, 200 °F, 250° F, 300 °F, 350 °F, 375 °F, 400 °F and 425 °F ( 66, 93, 121, 149, 177, 191, 204 and 218 °C), the combustion turbine power output, the combustion turbine heat rate and the plant power output and the corresponding heat rate are determined for each target fuel temperature. For each configuration, the heat transfer surface required to heat the fuel gas to the given target temperatures are also determined and budgetary price quotes are obtained for the fuel gas heaters. As expected, as the fuel temperature is increased, the overall efficiency (therefore the heat rate) improved, however at the expense of some small power output loss. Factoring in the fuel cost savings, the opportunity cost of the power lost, the cost of the various size performance heaters and the incremental auxiliary power consumption (if any), a cost-benefit analysis is carried out and the economically optimum fuel temperature and the corresponding performance heater size are determined for each 1×1×1 configuration.

scholarly journals Application of Heavy Fuel Test Results to Gas Turbine Operation

1982 ◽  
Author(s):  
R. S. Rose ◽  
A. Caruvana ◽  
A. Cohn ◽  
H. Von Doering
Keyword(s):  
Gas Turbine ◽  
Operating Conditions ◽  
Ash Deposition ◽  
Test Results ◽  
General Electric ◽  
Demonstration Program ◽  
On Line ◽  
Actual Field ◽  
Ash Removal ◽  
Stage 1

The results of ash deposition tests with simulated residual oil are presented. Both air-cooled and water-cooled nozzles were tested over a range of firing temperature, fuel contaminant levels, and metal surface temperatures. Extensive ash cleaning tests were also completed under full, steady-state operating conditions. Various online ash removal techniques were tested including small nutshells, large nutshells, coke particles, and water droplets. The results of these tests were applied to a General Electric gas turbine to predict actual field operation at turbine inlet temperatures up to 2300°F (1260°C). Use of on-line ash removal and optimum water washing intervals are shown to significantly improve the economics of gas turbine operation on heavy fuels. The improvements in heavy fuel operation were larger with a water-cooled stage 1 nozzle than with an air-cooled nozzle. This work was jointly sponsored by the Electric Power Research Institute and General Electric under the Advanced Cooling, Full-Scale Engine Demonstration Program.

scholarly journals Alternate Ways of Using Bottoming Cycle Power in Pipeline Gas Compressor Stations

1979 ◽  
Author(s):  
R. J. Rossbach
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Heat Rate ◽  
Department Of Energy ◽  
General Electric ◽  
General Electric Company ◽  
Target Value ◽  
Electric Company ◽  
Cycle Systems ◽  
Prime Movers

The General Electric Company is carrying out a design study and evaluation of bottoming cycles for gas pipeline compressor prime movers. Three sites were chosen for the study of demonstration organic bottoming cycles of about 5000 hp applied to three aircraft derivative gas turbines of approximately the same size. The purpose of the study is to design and evaluate all important aspects of installing organic bottoming cycle systems on a selected group of gas turbine prime movers driving gas compressors. As a result of the study, it was found that pipeline bottoming cycles applied to gas turbine prime movers could reduce the heat rate 35 percent more than the Department of Energy target value of 20 percent. Installation designs for three sites are described.

Vacuum Plasma Spray Turbine Bucket Coating Development

1985 ◽  
Author(s):  
J. H. Wood ◽  
P. W. Schilke ◽  
M. F. Collins
Keyword(s):  
Low Temperature ◽  
Gas Turbine ◽  
Plasma Spray ◽  
Hot Corrosion ◽  
Development Work ◽  
Vacuum Plasma Spray ◽  
Test Results ◽  
General Electric ◽  
Vacuum Plasma ◽  
Turbine Bucket

This paper describes the vacuum plasma spray (VPS) turbine bucket coating development work conducted by the General Electric Company, Gas Turbine Division. The potential for corrosion in gas turbine buckets is described, and examples of the different types of hot corrosion are shown. Development of the first VPS coating (PLASMAGUARD* GT-29) is discussed, and corrosion laboratory burner test and field test results are presented. Coating development work aimed at low-temperature hot-corrosion conditions is also summarized. Laboratory test results on a new PLASMAGUARD coating (GT-43) developed for low-temperature hot corrosion are presented. The new General Electric Gas Turbine Division VPS coating manufacturing facility used to apply these coatings is also described.

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