Search Results

Three Model Propulsion Simulators (MPS) were designed and built to evaluate candidate counterrotation Ultra bypass fan model blade designs of nominally 2-ft. (0.61m) tip diameter for an advanced “pusher-type” aircraft engine. These propulsion simulators (nominally 1/5 engine size) are capable of operation over a wide range of subsonic conditions and can deliver up to 750 shaft horsepower per rotor at rotor speeds of 10,000 rpm. The rotor thrust and torque, dynamic blade stresses, and system temperature data are transmitted through an integral telemetry system to facilitate data acquisition. Salient features of the design, instrumentation, and operation of these simulators are described in this paper.

Process capability information, combined with simplified component geometric models and assembly variation transfer functions built from Monte Carlo simulations, can give aircraft designers early estimations of product variability. Such predictions traditionally must wait for detailed component designs-after many important sourcing and production decisions have been made and when alternative designs are no longer an option. An additional benefit of early variation analysis is identification of major contributors to critical assembly variation. This information can alert downstream part designers of potential problem areas and also identify key manufacturing processes capabilities that must be verified, measured, and/or improved. This paper presents an efficient, top-down approach to move assembly variation analysis into early stages of aircraft development.

This paper accentuates the need for standards for airborne medical power supply system (AMPSS) installations. Potential electrical shock hazards through improperly designed AMPSS are discussed. The airplane electrical power system and the airplane environment are described and compared to that of a hospital. Regulatory bodies and medical device industry standards are discussed. Design safety requirements contained in the National Electric Code and ASTM standard for ground ambulances are identified. Federal regulations and standards for fixed wing medical transport units are compared to the above mentioned standards to demonstrate the lack of guidance material for medical airborne applications. This paper recommends that associations such as ASTM or SAE begin development of a standard for airborne applications based on existing standards.

At the request of the FAA, a committee was formed by the RTCA organization to prepare a Minimum Operating Performance Standard (MOPS) for Rechargeable Aircraft Lithium Battery Systems. This committee has being working for the last 2 years and completed the final draft during their 6th meeting in February 2008. Lithium Battery approval will be different than Nickel-Cadmium and Lead-Acid in that they will incorporate additional safety and documentation requirements. The MOPS, to be used by the FAA as the basis for a Technical Standard Order (TSO), includes the testing and evaluation criteria required for rechargeable lithium battery systems airworthiness demonstration.

In aircraft assembly, a burr left at the interface of any joint is considered a source of potential fatigue life degradation. Burrs can act as an additional stress concentration, leading to fretting, inducing failures. It could also open moisture paths resulting in corrosion. Burrs can affect the fatigue life of various structures differently depending on the type of joint, material, fastener, and installation process. Traditionally, we have disassemled and deburred the interface with various tools such as sand paper, file, chamfer tool, hook, or other tools. Disassembly and deburring of airplane major parts are time consuming and costly. In addition achieving “one up assembly” is not viable unless interfacial burr can be eliminated or reduced to the point where it will not affect fatigue life. In this investigation, the possibility of “one up assembly” via creation of concentric and adjacent clamping in various materials is studied.

Advancements in commercial aircraft batteries have been driven by changes in licensing requirements. Early model aircraft needed batteries to comply with a five minute emergency power requirement. This short time requirement was later incremented to 30 minutes and was recently increased to one hour. These requirements have changed to meet the demands of emergency equipment which, over time, have grown in sophistication and number. Traditional flight-by-cable aircraft require emergency power mostly for instrumentation to help reach a zone were continued visual flight and landing is possible. With the advent of flight-by-wire aircraft, emergency power is not only necessary for instrumentation, but is critical to flight itself. There is no single method for choosing a battery. The requirements for a battery will depend on many factors, including the availability of alternate sources of emergency power.

This paper presents results of mass flow prediction study in progressive bore throttle body (TB), using CFD. A major emphasis of the study has been on capturing the effect of tolerance on clearance area and hence flow predictions, especially at low angles. In addition, effect of viscosity on mass flow predictions has been investigated. Comparison of experimental mass flow obtained from a “manufactured TB” with CFD prediction leads to significant difference, especially at low angles. One reason for this difference is that CFD models based on mean-CAD geometry do not capture the effect of tolerances. To address this difference, an analytical equation for predicting clearance area has been developed. This allows capturing of variation in geometry due to manufacturing. A Design of Experiments (DoE) approach utilizing the analytical work and GE proprietary six sigma tools has been used to capture the effect of tolerances on the clearance area and quantify the variation.

Radio Technology Commission for Aeronautics (RTCA) at the request of the Federal Aviation Administration (FAA) formed a committee to prepare a Minimum Operating Performance Standard (MOPS) for aircraft batteries. The MOPS was limited to rechargeable and starting batteries as power sources for equipment installed in aircraft. This committee has being working for the last 3 years and completed the final draft during their 6th meeting in April 2004. The MOPS, to be used by the FAA as the base for a Technical Standard Order (TSO) in preparation, includes the testing and evaluation criteria required for secondary Lead-Acid (Pb-A) and Nickel-Cadmium (Ni-Cd) batteries airworthiness demonstration.

This paper reviews powerplant operational and maintenance procedures with the objective of minimizing fuel consumption and total operating costs of existing large turbofan engines. Specific recommendations are made to reduce the rate of on-wing performance deterioration and to define cost effective performance refurbishment. Measures being taken to accomplish further fuel and cost savings in the future are summarized. These include design performance retention improvements and development of per-formance diagnostic/analytical systems to permit better management control of engine operating costs.

Significant design features of the thrust reverser and spoiler of the CF6 engine (powerplant for the McDonnell Douglas DC-10) are described, along with the design impact of major requirements including maintainability and noise reduction. Also included is the development test program which is designed to provide accelerated component and system evaluation.

A completely hermetic refrigeration system can be one of the viable candidates for minimizing CFC emissions currently being released from automotive air conditioning systems which utilize an open type compressor with shaft seal and rubber hoses. A series of system simulator tests and vehicle heat chamber tests was conducted using a prototype semi-hermetic scroll compressor with a brushless motor and a specially modified alternator. A conventional fixed displacement compressor was used in the original air conditioning system as a baseline, and the proposed electric system was evaluated on the same car to attain a comparable cooling performance. Heat influx to the passenger compartment was reduced by applying glazing film and insulation material, and the heat dissipation was increased by a high performance condenser. Several other factors to determine the feasibility of this new system are also discussed.

To support an industry wide response to an EASA proposed Special Condition regarding the threat of in-flight supercooled liquid water icing conditions at altitudes above FL300, Boeing 777 fleet data were used to estimate the frequency and severity of such icing occurrences. The data were from the calendar year 2019 and included ~ 950,000 airline revenue flights from around the world by multiple operators. The unique architecture of the Primary Ice Detection System (PIDS) on that model, in addition to robust meteorological data that was able to be correlated, afforded an opportunity to conservatively estimate the Total Water Exposure (TWE) and thus the Liquid Water Content (LWC) of the icing encounters captured at FL295 and above. This paper will outline the key methods used and present the findings.

A Computer Aided Process Planning (CAPP) system is being implemented in the manufacture of rotating components for aircraft engines. The system provides a process planning data base and a set of computerized techniques, all easily accessible from a multiple function computer graphics work station. This paper briefly describes the use of CAPP as contrasted with the traditional approach to process planning. The development of the system, the technologies involved in its design, and the implementation approach are also discussed.

Members of supply chains face many conflicts between the efficient operation of the individual unit and the demands of membership in the supply chain. What is good for the Link isn't always good for the Chain. This paper addresses the conflicts and suggests sharing both risks and profits as a breakthrough solution that integrates tactics (the method of operations of the link) with strategy (the method of operations of the chain). Additional elements necessary to achieve the success are also discussed.