scholarly journals CFM56 Turbofan Engines: General Electric/SNECMA Cooperative Engineering Development Program

1976 ◽  
Author(s):  
E. Caffier ◽  
A. O. Kohn
Keyword(s):  
Development Program ◽  
The United States ◽  
Preliminary Design ◽  
General Electric ◽  
General Electric Company ◽  
Turbofan Engine ◽  
Turbofan Engines ◽  
Design Activities ◽  
Interface Definition ◽  
And Control

General Electric Company, USA, and the Societe Nationale d’Etude et de Construction de Moteurs d’Aviation (SNECMA), France, have formed a joint company to develop a “ten ton” high bypass turbofan engine for the commercial and military markets that are expected to exist in the late 1970’s and the 1980’s. Overall program management, marketing, engineering, production, and product support are elements that have been defined to make this program workable. This paper deals with the management of the engineering aspects of the development program and describes the division of responsibilities, interface definition and control, integration and communications, requirements and security aspects of the program. The program was started in 1971 and preliminary design activities were conducted for several years. Hardware design and development started in 1973 and now four engines are on test, two in the United States and two in France. Experience to date indicates that barriers of distance and language are being overcome and that this type of program can be successful.

scholarly journals The CFM56 Engine Family: An International Development

1988 ◽  
Author(s):  
L. M. Spence ◽  
Georges Sangis
Keyword(s):  
United States ◽  
International Development ◽  
The United States ◽  
Market Opportunity ◽  
General Electric ◽  
Turbofan Engine ◽  
Engine Family ◽  
Total Investment

During the 1970’s General Electric of the United States and Societe Nationale d’Etude et de Construction de Moteurs d’Aviation (SNECMA) of France took advantage of a unique market opportunity to develop a modern, fuel efficient, quiet turbofan engine in the 20000 to 25000# thrust class. Both companies had confidence that there would be a significant demand for such an engine to warrant the large total investment of both money and resources.

The Effect of Environmental Regulations on the General Electric Research and Development Program for Combustion Turbines Using Coal-Derived Fuels

1979 ◽  
Author(s):  
N. R. Dibelius ◽  
R. J. Ketterer ◽  
G. B. Manning
Keyword(s):  
Research And Development ◽  
Development Program ◽  
Clean Air Act ◽  
Department Of Energy ◽  
Clean Water ◽  
General Electric ◽  
General Electric Company ◽  
Gaseous Fuels ◽  
Electric Company ◽  
Clean Air

This paper discusses the Clean Air Act, the Clean Water Act, and Noise Control Act as they affect stationary combustion turbines, including combustion turbines on coal-derived liquid and gaseous fuels. It also includes a discussion of regulations resulting from these acts insofar as they existed as of July, 1978. New regulations are being added periodically. This situation will continue and, therefore, requires that the most recent regulations be consulted for any given case. The views expressed in this paper are those of the authors and do not necessarily represent those of the Department of Energy or General Electric Company.

The United States Supersonic Transport A Progress Report

1968 ◽  
Vol 72 (691) ◽  
pp. 567-573
Author(s):  
John M. Swihart
Keyword(s):  
United States ◽  
Federal Aviation Administration ◽  
The United States ◽  
Progress Report ◽  
General Electric ◽  
General Electric Company ◽  
Supersonic Transport ◽  
Electric Company ◽  
Intense Competition ◽  
Boeing Company

On 31st December 1966, General McKee of the Federal Aviation Administration announced that The Boeing Company and the General Electric Company had been selected to develop the prototype airframe and engines for the United States supersonic transport. The announcement ended a long, intense competition and was the culmination of the nine years of effort on the part of Boeing, where since January 1958 there has been an identified, separate project devoted to the SST.

Status Report of the Turbofan Engine Development Program in Japan

1977 ◽  
Author(s):  
M. Matsuki ◽  
T. Torisaki ◽  
K. Miyazawa ◽  
M. Itoh
Keyword(s):  
Research And Development ◽  
Development Program ◽  
Status Report ◽  
Second Phase ◽  
Turbofan Engine ◽  
Turbofan Engines ◽  
The Status ◽  
Target Performance ◽  
Bypass Ratio ◽  
Engine Development

A National Research and Development Program of high bypass ratio turbofan engines has been in process in Japan since 1971. Target performance characteristics of the first-phase 5-ton thrust class engines have been attained, and development of the second-phase engines has been started in 1976. This paper reviews the status of the program, discusses some engineering progress attained, and presents an outline of the second-phase program and engines.

scholarly journals Status of Joint General Electric-Maritime Administration Heavy Duty Gas Turbine Development Program

1973 ◽  
Author(s):  
S. M. Kaplan ◽  
H. Helfenstein
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
The United States ◽  
Maritime Industry ◽  
Heavy Duty ◽  
General Electric ◽  
The Status ◽  
Development Goals ◽  
Heavy Duty Gas Turbine ◽  
Turbine Design

The United States Maritime Administration and the Gas Turbine Products Division of the General Electric Company have joined in a five-year, cost-sharing program to promote the domestic maritime industry using improved concepts of heavy duty gas turbine design. This paper describes the elements of that program and reports on the progress at its midpoint, two and one-half years following its inception. The status of project development goals and technical attainments to date indicate that the contractual objectives of both parties are being attained.

scholarly journals Evaluation of a Water-Cooled Gas Turbine Combined Cycle Plant

1978 ◽  
Author(s):  
A. Caruvana ◽  
W. H. Day ◽  
G. B. Manning ◽  
R. C. Sheldon
Keyword(s):  
Gas Turbine ◽  
The United States ◽  
Combined Cycle ◽  
Preliminary Design ◽  
Plant Design ◽  
General Electric ◽  
Design Work ◽  
Combined Cycle Plant ◽  
And Performance ◽  
The Impact

General Electric initiated the development of a water-cooled gas turbine in the early 1960’s. The first laboratory model of a water-cooled rotor, 9.7 in. (24.7 cm) was successfully tested in 1973 at sustained firing temperatures of 2850 F (1556 C) and 16 atm pressure while maintaining bucket surface temperatures of 1000 F (583 C) or less. Maximum firing temperatures of 3500 F (1927 C) were also attained during this period. The Electric Power Research Institute (EPRI) funded initial preliminary design work which utilized the water-cooled turbine concept in a combined cycle starting in 1974. Development work to define and resolve potential barrier problems was also funded by EPRI in the original and subsequent follow-on contracts. The United States Energy Research and Development Administration (ERDA) awarded a contract to the General Electric Company in May 1976 to conduct a preliminary design study which incorporates the water-cooled gas turbine concept in a combined cycle plant. The design is based on a gas turbine firing temperature (gas temperature entering the first-stage buckets) of 2600 F (1427 C) utilizing a coal-derived low-Btu gas or coal-derived liquid. This paper presents the results of the ERDA Program. Particular emphasis is devoted to the description of the overall plant design and performance. Turbine subsystems of the water-cooled concept and the alternate cooling concepts considered are also presented in this paper. The operating features and characteristics of an advanced fixed-bed gasifier and associated gas cleanup systems are also discussed relative to the impact on the overall system design and performance.

The F-16 Common Engine Bay

1985 ◽  
Author(s):  
C. E. Porcher
Keyword(s):  
United States Air Force ◽  
The United States ◽  
Organizational Level ◽  
General Electric ◽  
Engine Model ◽  
Technology Corporation ◽  
General Dynamics ◽  
Engine Mount ◽  
Interface Definition ◽  
Whitney Aircraft

In 1979 the United States Air Force elected under the Engine Model Derivative Program (EMDP) to explore derivative engine concepts by the General Electric Company and the Pratt and Whitney Aircraft Division of United Technology Corporation with the objective of improving engine durability and reducing engine ownership cost for future procurements of their first line fighter engines. Concurrently, General Dynamics was invited to develop the necessary airframe/engine interface definition to assure engine compatibility with the airplane requirements. This EMDP development culminated in 1981 with the Alternate Fighter Engine (AFE) competition with General Electric proposing the F110-GE-100 engine and Pratt and Whitney Aircraft proposing the F100-PW-220. Both engines were placed in Full Scale Development and both met the USAF objectives of 4000 TAC cycle life and improved engine cost and warranty for application to the F-15 and F-16 fighters. General Dynamics evolved the concept of the Common Engine Bay which has all aircraft interfaces compatible with either AFE engine and the current Pratt and Whitney Aircraft F100-PW-200 engine. The original F-16 nacelle design, with minor modification of the interfaces and engine mount structure, was adapted to permit full interchangeability for the F100-PW-200, F100-PW-220, or the F110-GE-100 engines. Design requirements were set to permit a common airplane with no break in the production line or aircraft model change and with appropriate simple kits to permit interchangeability of any of the three engines in the field at the organizational level. This manufacturing capability allows the USAF the flexibility to conduct subsequent competitive procurement of the engine.

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