A Market Research Effort Leading to the Development of a High Efficiency 10,000 shp Gas Turbine System

This paper describes the market research efforts which established the performance parameters, the design criteria and the product specification for a new 10,000 shp regenerative cycle gas turbine system which incorporates a two-stage intercooled centrifugal compressor and features a thermal efficiency which exceeds 43 percent.

Aerodynamic Design and Testing of an Improved 1st Stage Compressor Rotor for a Heavy Duty Gas Turbine

To evaluate the potential of the compressor of Sulzer’s Typ 3 gas turbine, a series of engine tests was analyzed with two computer codes. The comparison between measured and calculated performance map are given in the paper. The design goal was to find modifications, which can be applied easily to already operating engines. The simplest option-increase of shaft speed with the existing blades-would have caused high loss due to increased tip Mach number. The calculation revealed, that a newly designed first rotor blade is an appropriate modification to increase massflow and efficiency. No further change is required, because the calculations indicate, that all subsequent stages operate at near optimum incidence. The calculations were confirmed experimentally. The paper presents the new rotor blade and its influence on the compressor calculated and measured performance.

Low NOx Combustion Systems for Burning Heavy Residual Fuels and High-Fuel-Bound Nitrogen Fuels

The work described in this paper is a part of the Department of Energy/Lewis Research Center (DOE/LeRC) “Advanced Conversion Technology” (ACT) project. The program is a multiple contract effort with funding provided by the Department of Energy and technical program management provided by NASA. LeRC. Environmentally acceptable operation with minimally processed petroleum based heavy residual and coal derived synthetic fuels requires advanced combustor technology. The technology described in this paper was developed under the DOE/ NASA Low NOx Heavy Fuel Combustor Concept Program (Contract DEN3-145). Novel combustor concepts were designed for dry reduction of thermal NOx, control of NOx from fuels containing high levels of organic nitrogen, and control of smoke from low hydrogen content fuels. These combustor concepts were tested by burning a wide variety of fuels including a middle distillate (ERBS), a petroleum based heavy residual, a coal derived synthetic (SRC-II), and various ratios of blends of these fuels.

A Study of External Fuel Vaporization

A conceptual design study was conducted to devise and evaluate techniques for the external vaporization of fuel for use in an aircraft gas turbine with characteristics similar to the Energy Efficient Engine (E3). A second purpose of the study was to select the most favorable fuel vaporization concept. In the study, three candidate concepts were analyzed from the standpoint of fuel thermal stability, integration of the vaporizer system into the aircraft engine, engine and vaporizer dynamic response, startup and altitude restart, engine performance, control requirements, safety, and maintenance. The results of the study indicate that an external vaporization system can be devised for an E3 -type engine with hardware of reasonable size. The hardware can be packaged without increasing the total engine volume and the system is not unduly complex. The selected concept offers potential gains in engine performance in terms of reduced specific fuel consumption and improved engine thrust/weight ratio. The thrust/weight improvement can be traded against vaporization system weight. However, the vaporizer is subject to fouling with deposits formed at the walls exposed to heated fuel.

Improved Particle Trajectory Calculations Through Turbomachinery Affected by Coal Ash Particles

Trajectories of small coal ash particles encountered in coal-fired gas turbines are calculated with an improved computer analysis currently under development. The analysis uses an improved numerical grid and mathematical spline-fitting techniques to account for three-dimensional gradients in the flow field and blade geometry. The greater accuracy thus achieved in flow field definition improves the trajectory calculations over previous two-dimensional models by allowing the small particles to react to radial variations in the flow properties. A greater accuracy thus achieved in the geometry definition permits particle rebounding in a direction perpendicular to the blade and flow path surfaces rather than in a two-dimensional plane. The improved method also accounts for radial variations in airfoil chord, stagger, and blade thickness when computing particle impact at a blade location.

Control System for the Mainline Gas Turbines and Crude Oil Pumps on the Saudi Arabian Petroline

The paper presents an overview of the system employed to control the mainline gas turbines and crude oil pumps used on the 747 mile East-West Petroline. Various operating modes such as starting, stopping and fuel transfers for normal and emergency operation are discussed. Particular attention is focused on the various fuel systems as well as a review of the major design problem areas and solutions. The results of a system test and the integration of each unit into the overall pipeline control scheme are included for completeness.

Re-Examination of Design Criteria for Natural Gas Compressorstation “Ravenstein”: Holland

During the initial years of Gasunie’s existence, the early 60’s, a projection was made for the power required in various compressorstations in the grid. This projection was updated periodically and this paper reviews the 1977 update, focussing on the Ravenstein compressorstation. The main subject of the paper is the development of the design criteria for this update and the comparison with the reality of the 1979/1980 pumping season. It may be stated that the actual conditions of the pumping season have justified the selection of the criteria.

Preliminary Design of Dry Cooling Tower for the Closed Cycle Gas Turbine HTGR

Because of its relatively high coolant temperature, the closed cycle gas turbine HTGR is well adapted to dry cooling and its waste heat can be rejected with relatively low cost. The preliminary design of natural-draft dry cooling towers for a 1200 MW(e) GT-HTGR is presented. The effects of air approach velocity, capacity rates of air and water mediums, and number of heat exchanger cross flow passes on salient tower and heat exchanger dimensions are studied. Optimum tower designs are achieved with three cross flow passes for the heat exchanger, resulting in a simultaneous minimization of tower height, heat exchanger surface area and circulating water pumping power. Four alternative tower designs are considered and their relative merits are compared. It is concluded that the 1200 MW(e) plant can be cooled by a single tower design which is well within the present state of the natural-draft dry cooling tower technology. In comparison, the fossil-fired or HTGR steam plants of the same output is shown to need three such towers.

Test Verification of Water Cooled Gas Turbine Technology

This paper presents the results of three significant tests recently performed by GE under the DOE High Temperature Turbine Technology Phase II Program contract. The first test involved a simulated Integrated Gasification Combined Cycle (IGCC) test of a water-cooled composite nozzle exposed to low Btu coal gas at design operating conditions (2600 F + firing temperature, 12 atm pressure). The second test is that of a water-cooled monolithic nozzle, a full-scale model of the second-stage nozzle planned for the Technology Readiness Vehicle Verification Test. The third test demonstrates coolant water delivery, transfer, and metering distribution, from the stationary feed line to the turbine rotor, enroute to individual bucket airfoil coolant passages. These tests successfully demonstrated the IGCC operation with very good results, and show every indication that operation at firing temperatures up to 3000 F is well within the design capability of the water-cooled turbine.

Contamination of Centrifugal Process Gas Compressor Lube Oil and Seal Oil Systems by Hydrocarbon Condensate

In the wake of gas compression offshore the problem of contamination of Seal Oil and Lube Oil systems by the process gas has posed particular problems. These difficulties stem chiefly from the uniqueness of the offshore situation, viz.: The inability to “waste” contaminated seals return because of an uncertain supply situation (oil inventory bunkered by boat) and the twin constraints of weight space restrictions imposed by offshore design. “In situ” treatment of relatively large volumes of contaminated Lube Oil and Seal Oil on offshore platforms is possible using the method described in this paper.