Highlights of Roy Smith’s Career at General Electric

2012 ◽  
Vol 134 (6) ◽  
Author(s):  
C. C. Koch
Keyword(s):  
Gas Turbine ◽  
Design Theory ◽  
Product Line ◽  
Special Session ◽  
Aerodynamic Design ◽  
General Electric ◽  
Theory Analysis ◽  
Jet Engine ◽  
Asme Turbo Expo ◽  
The Many

Dr. Leroy H. (Roy) Smith, Jr. of General Electric (GE) was honored at a special session of the ASME Turbo Expo 2009 in recognition of his 55 years of contributions to the gas turbine industry. Although best known to his ASME and International Gas Turbine Institute (IGTI) colleagues for his many publications on compressor aerodynamic design theory, analysis methods, and research, he has made equally impressive contributions to GE’s jet engine product line. This paper gives a brief chronology of his career, then focuses on the many outstanding fan and compressor aero designs he has created for several major GE engine families.

Highlights of Roy Smith’s Career at GE

2009 ◽  
Author(s):  
C. C. Koch
Keyword(s):  
Gas Turbine ◽  
Design Theory ◽  
Product Line ◽  
Special Session ◽  
Aerodynamic Design ◽  
General Electric ◽  
Theory Analysis ◽  
Jet Engine ◽  
Asme Turbo Expo ◽  
The Many

Dr. Leroy H. (Roy) Smith, Jr. of General Electric is to be honored at a special session of the ASME Turbo Expo 2009 in recognition of his 55 years of contributions to the gas turbine industry. Although best known to his ASME and IGTI colleagues for his many publications on compressor aerodynamic design theory, analysis methods and research, he has made equally impressive contributions to GE’s jet engine product line. This paper gives a brief chronology of his career, then focuses on the many outstanding fan and compressor aero designs he has created for several major GE engine families.

Certification of Mechanical-Drive Gas Turbine Packages for Installation in Hazardous Locations

1983 ◽  
Author(s):  
J. C. McMullen ◽  
R. Dundas
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Product Line ◽  
Third Party ◽  
General Electric ◽  
Special Equipment ◽  
General Electric Company ◽  
Electric Company

It is becoming increasingly more difficult to obtain local jurisdictional approval for the installation of gas turbines in hazardous locations. This is occurring because of changes to codes and standards, the reluctance of inspectors to make judgments on special equipment, and the requirements for third party certifications in countries other than the country of manufacture. The Gas Turbine Division of General Electric Company has initiated a program to review, upgrade, and certify its mechanical drive product line for installation in hazardous locations. The special requirements and problems of the program, as well as its implementation, are discussed.

scholarly journals Sir William Rede Hawthorne. 22 May 1913—16 September 2011

2018 ◽  
Vol 66 ◽  
pp. 309-328
Author(s):  
E. M. Greitzer ◽  
D. E. Newland
Keyword(s):  
Gas Turbine ◽  
Royal Society ◽  
Secondary Flows ◽  
Leadership Roles ◽  
Strong Ties ◽  
Jet Engine ◽  
The Us ◽  
Engineering Department ◽  
The Many ◽  
Gas Turbine Cycle

William Rede Hawthorne was a pioneer in gas turbine aerodynamics and thermodynamics, a sought-after technology advisor to industry and government, and a generous and enthusiastic teacher who encouraged students to excel. His outstanding contributions included resolution of combustion problems that limited the operation of the original Whittle jet engine, early in-depth descriptions of compressible channel flow that still inform engineers today, innovative and wide-ranging analyses of secondary flows in turbomachinery that defined the field, and creation of some of the first notes on gas turbine cycle analysis. A theme in the many areas of engineering in which he had impact was the satisfaction from the growth of understanding that can accompany making things work—in his words, ‘machines produce ideas just as surely as ideas produce machines’. A Cambridge graduate, he was a professor at MIT when, in 1951, he was recruited to a newly established chair at Cambridge, where he later had leadership roles as head of the engineering department (1968–73) and Master of Churchill College (1968–83). He retained strong ties to MIT, however, and fostered lasting collaborations between the two universities. Among his numerous awards and honours were the US Medal of Freedom (1947), a Royal Society Medal (1982) and a knighthood (1970) for ‘services to thermodynamics’, a citation that pleased him greatly.

CM-R 411

Alloy Digest ◽  
1967 ◽  
Vol 16 (9) ◽  
Keyword(s):  
Shear Strength ◽  
High Temperature ◽  
Gas Turbine ◽  
Precipitation Hardening ◽  
Base Alloy ◽  
Heat Treating ◽  
Nickel Base Alloy ◽  
Jet Engine ◽  
Temperature Performance ◽  
Nickel Base

Abstract CM-R41 is a vacuum-melted, precipitation hardening nickel-base alloy possessing outstanding properties in the temperature range of 1200 F to 1800 F. It is recommended for jet engine and gas turbine components operating at high temperatures. This datasheet provides information on composition, physical properties, elasticity, tensile properties, and shear strength as well as creep. It also includes information on high temperature performance as well as forming, heat treating, machining, and joining. Filing Code: Ni-127. Producer or source: Cannon-Muskegon Corporation.

CARPENTER M-252

Alloy Digest ◽  
1973 ◽  
Vol 22 (9) ◽  
Keyword(s):  
Corrosion Resistance ◽  
High Temperature ◽  
Physical Properties ◽  
Gas Turbine ◽  
Base Alloy ◽  
Heat Treating ◽  
Nickel Base Alloy ◽  
Jet Engine ◽  
Temperature Performance ◽  
Nickel Base

Abstract CARPENTER M-252 is an age-hardenable nickel-base alloy designed for highly stressed parts operating at temperatures up to 1600 F. Its prime application is for jet-engine and gas-turbine buckets. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as creep. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, machining, and joining. Filing Code: Ni-195. Producer or source: Carpenter.

CMN-155

Alloy Digest ◽  
1968 ◽  
Vol 17 (8) ◽  
Keyword(s):  
High Temperature ◽  
Heat Resistance ◽  
Physical Properties ◽  
Gas Turbine ◽  
Base Alloy ◽  
Heat Treating ◽  
Jet Engine ◽  
Iron Base Alloy ◽  
Temperature Performance ◽  
High Oxidation

Abstract CMN-155 is an austenitic iron-base alloy having high oxidation and heat resistance combined with good high temperature properties. It is recommended for jet engine and gas turbine components, high temperature fasteners, and rocket chambers. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as creep. It also includes information on high temperature performance as well as forming, heat treating, machining, and joining. Filing Code: SS-212. Producer or source: Cannon-Muskegon Corporation.

Transformation of an Aviation Turboshaft Engine Into a Experimental Jet Engine for Laboratory Testing Unstable Radial Compressor Work

2014 ◽  
Author(s):  
Marián Hocko ◽  
Jiri Polansky
Keyword(s):  
Gas Turbine ◽  
Experimental Testing ◽  
Thermodynamic Characteristics ◽  
Power Generator ◽  
Jet Engine ◽  
Radial Compressor ◽  
Laboratory Device ◽  
Research And Education ◽  
Turboshaft Engine ◽  
Electronic Elements

The article deals with the use of a small aviation turboshaft engine for laboratory purposes. This study describes its transformation into an experimental device for research and education. Various constructional, technological and controlling modifications and settings of the gas turbine test stand were carried out and tested on a stationary configuration. The stationary system can be used as a small backup power generator or as a drive unit for a compressor, pump, etc. New control systems, electronic elements and methods of measuring rotations, pressure and temperature are tested for educational and research purposes. The study includes a schematic description of modelling measurements and subsequent numerical evaluation of the thermodynamic characteristics of the cycle in an experimental gas turbine. The laboratory device presented here is, thanks to technological, material and thermodynamic research, suitable for educating and testing the knowledge of future aviation and mechanical engineers. The content of the article is a description of the use of transformed small turboshaft engine into small jet engine by means of experimental testing of unstable work of the radial compressor under laboratory conditions.

Mixing of Exhaust and By-pass Flow in a By-pass Engine

1962 ◽  
Vol 66 (620) ◽  
pp. 528-530 ◽  
Author(s):  
H. Pearson
Keyword(s):  
Gas Turbine ◽  
Combustion Temperature ◽  
Propulsive Efficiency ◽  
Jet Engine ◽  
Equivalent Result ◽  
Jet Velocity ◽  
Cycle Efficiency

It is well known that the main purpose of the by-pass principle is to improve the propulsive efficiency of a simple jet engine by removing some of the energy left in the jet gases and using this to compress an extra quantity of air, known as the by-pass air, this air being ejected rearwards with the jet gases. In this way a greater mass of air is ejected rearwards at a lower jet velocity and thus a better propulsive efficiency is obtained. This is an extremely simplified view of the advantages of the by-pass engine, however, since an equivalent result of obtaining a lower jet velocity can be obtained by designing the jet engine for a lower combustion temperature. The by-pass principle is of advantage because it enables a higher propulsive efficiency to be obtained at the same time as employing a high combustion temperature and therefore a high basic cycle efficiency. If the component efficiencies of a gas turbine were 100 per cent, cycle efficiency would not depend upon combustion temperature at all, and there would thus be no advantage in principle in using the by-pass engine. In practice there would probably be some residual advantage left in that for a given thrust a lower engine weight could be obtained.

Performance Improvement Program for Kawasaki Gas Turbine

2017 ◽  
Author(s):  
Tomoki Taniguchi ◽  
Ryoji Tamai ◽  
Yoshihiko Muto ◽  
Satoshi Takami ◽  
Ryozo Tanaka ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Thermal Performance ◽  
Film Cooling ◽  
Gas Turbines ◽  
Large Scale ◽  
New Technologies ◽  
Design Procedure ◽  
Product Line ◽  
Combined Cycle ◽  
Improvement Program

Kawasaki Heavy Industries, Ltd (KHI) has started a comprehensive program to further improve performance and availability of existing Kawasaki gas turbines. In the program, one of the Kawasaki’s existing gas turbine was selected from the broad product line and various kinds of technology were investigated and adopted to further improve its thermal performance and availability. The new technologies involve novel film cooling of turbine nozzles, advanced and large-scale numerical simulations, new thermal barrier coating. The thermal performance target is combined cycle efficiency of 51.6% and the target ramp rate is 20% load per minute. The program started in 2015 and engine testing has just started. In this paper, details of the program are described, focusing on design procedure.

scholarly journals Development of the PGT 25 High Efficiency Gas Turbine: Part 2 — Aerodynamic Design and Performance

1984 ◽  
Author(s):  
E. Benvenuti ◽  
B. Innocenti ◽  
R. Modi
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Performance Testing ◽  
Operating Conditions ◽  
Aerodynamic Design ◽  
Direct Drive ◽  
Gas Generator ◽  
Full Load ◽  
Wide Range ◽  
Overall Performance

This paper outlines parameter selection criteria and major procedures used in the PGT 25 gas turbine power spool aerodynamic design; significant results of the shop full-load tests are also illustrated with reference to both overall performance and internal flow-field measurements. A major aero-design objective was established as that of achieving the highest overall performance levels possible with the matching to latest generation aero-derivative gas generators; therefore, high efficiencies were set as a target both for the design point and for a wide range of operating conditions, to optimize the turbine’s uses in mechanical drive applications. Furthermore, the design was developed to reach the performance targets in conjunction with the availability of a nominal shaft speed optimized for the direct drive of pipeline booster centrifugal compressors. The results of the full-load performance testing of the first unit, equipped with a General Electric LM 2500/30 gas generator, showed full attainment of the design objectives; a maximum overall thermal efficiency exceeding 37% at nominal rating and a wide operating flexibility with regard to both efficiency and power were demonstrated.

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