Observations of Flame Behavior From a Practical Fuel Injector Using Gaseous Fuel in a Technology Combustor

This paper presents results from an Air Force program being conducted by researchers at Brigham Young University (BYU) Wright-Patterson Air Force Base (WPAFB), and Pratt and Whitney Aircraft Co (P&W). This study is part of a comprehensive effort being supported by the Aero Propulsion and Power Laboratory at Wright-Patterson Air Force Base, and Pratt and Whitney Aircraft, Inc. in which simple and complex diffusion flames are being studied to better understand the fundamentals of gas turbine combustion near lean blowout. The program’s long term goal is to improve the design methodology of gas turbine combustors. This paper focuses on four areas of investigation: 1) digitized images from still film photographs to document the observed flame structures as fuel equivalence ratio was varied, 2) sets of LDA data to quantify the velocity flow fields existing in the burner, 3) CARS measurements of gas temperature to determine the temperature field in the combustion zone, and to evaluate the magnitude of peak temperature, and 4) two-dimensional images of OH radical concentrations using PLIF to document the instantaneous location of the flame reaction zones.

Microstructure of an extruded rapidly solidified Al-8Fe-2Mo alloy

Light weight materials which possess high strength and durability are being utilized by the automotive industry to increase fuel economy. Rapidly solidified (RS) Al alloys are currently being extensively studied for this purpose. In this investigation the microstructure of an extruded Al-8Fe-2Mo alloy, produced by Pratt & Whitney Aircraft, Goverment Products Div. was examined in a JE0L 2000FX AEM. Both electropolished thin sections, and extraction replicas were examined to characterize this material. The consolidation procedure for producing this material included a 9:1 extrusion at 340°C followed by a 16:1 extrusion at 400°C, utilizing RS powders which have also been characterized utilizing electron microscopy.

The F-16 Common Engine Bay

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.

The Potential Impact of Future Fuels on Small Gas Turbine Engines

The impact of potential aviation gas turbine fuels available in the near to midterm, is reviewed with particular reference to the small aviation gas turbine engine. The future course of gas turbine combustion R&D, and the probable need for compromise in fuels and engine technology, is also discussed. Operating experience to date on Pratt & Whitney Aircraft of Canada PT6 engines, with fuels not currently considered of aviation quality, is reported.

Interim Review of the Energy Efficient Engine (E3) Program

The status of the NASA sponsored Energy Efficient Engine Program, being conducted by Pratt & Whitney Aircraft, is reviewed. The current performance status is discussed; and the results of three technology programs, the shroudless fan, the segmented combustor and the mixer are reviewed. A projection is presented of the performance potential of the Energy Efficient Engine technology.

Jet Engine Computer Aided Tube Design System

At Pratt & Whitney Aircraft a system to design tubing, produce final engineering drawings and establish data for manufacturing was developed that effectively integrates man and computer. A “wire tube” defined on a wooden mockup is fed to a host computer to perform stress and vibration analysis and check clearance to other tubes and components. The tube is then retrieved from a data base, maintained on the host, by the Computervision system to produce final drawings. The data base is then available to manufacturing to drive an automatic tube bender.