Browse Topic: Cowlings

Items (22)

Improve Heat Resistance of Composite Engine Cowlings Using Ceramic Coating Materials, Experimental Design and Testing

01-11-01-000406/04/2018

A large amount of heat generated in the engineering compartment in a hovering helicopter may lead to premature degradation of inner skin of its engine cowling and cause serious failure on the engine cowling. This study proposes a solution of improving heat resistance of the helicopter engine cowlings by replacing the currently used intumescent coating with a ceramic coating material, Cerakote C-7700Q. Oven and flame tests were designed and conducted to evaluate the heat resistance of Cerakote C-7700Q. The test results show that the currently used painting scheme of the engine cowlings failed the 220°C oven test while after replacing the epoxy seal coat with the Cerakote, the new painting system passed the 220°C test in regards to painting bubbling. Based on that, a new painting scheme with C-7700Q implemented was recommended. It is suggested that the most time- and cost-effective solution to improve thermal performance of the helicopter engine cowlings is to repaint the current engine

Liu, Yucheng, Sippel, Thomas, He, Ge

Aircraft Tow Bar

ARP1915D (Historical)09/13/2010

This SAE Aerospace Recommended Practice (ARP) outlines the basic general design considerations for transport aircraft tow bars. It does not cover the requirements for tow bars intended for aircraft with a maximum ramp mass (MRW) below 8600 kg (19 000 lb).

AGE-3 Aircraft Ground Support Equipment Committee

Aircraft Damage Caused by Ground Support Equipment

AIR1589A (Historical)12/09/2009

Only those incidents where a piece of ground support equipment directly associated with the "turnaround" servicing of an aircraft was involved are reviewed. Specifically excluded are those incidents that occurred during heavy maintenance, overhaul activity, or aircraft taxiing.

AGE-3 Aircraft Ground Support Equipment Committee

Aircraft Tow Bar

ARP1915C (Historical)04/06/2005

AGE-3 Aircraft Ground Support Equipment Committee

Environmental Control System for Light Turbo Prop

2003-01-240007/07/2003

Honeywell has developed a unique environmental control system (ECS) for light turbo-prop aircraft applications. The ECS consists of two integrated systems, an Air Cycle System (ACS) and a Vapor Cycle Cooling System (VCCS). A single controller interfaces with both systems, and provides control by monitoring temperatures within the environment. The valves and fans of the ECS are then adjusted to provide the necessary control to minimise the error between the actual and set temperatures. The controller specifically provides the following functions: ACS control when selected on by the pilot VCCS control when selected on by the pilot Automatic ACS or VCCS control when selected by the pilot System self test The compressor used in the VCCS is a new generation compressor: 28Vdc power supply current Hermetical compressor technology Brush-less DC motor Analogical driving speed This paper will present the design of the hybrid ACS/VCCS environmental control system and notably its unique

Genty, A., Saunders, A., Cimino, J. P., Rose, S.

Cessna establishes its Sovereignty

AEROAPR02_0604/01/2002

The company finalizes development of the Sovereign and prepares it for FAA certification, which is expected late this year. Engineers at Cessna Aircraft Co. recently conducted the first engine run for the Sovereign. The aircraft's power plant is one of the few remaining systems being tested prior to first flight, which is scheduled for early spring. FAA certification is expected to be awarded in late 2003, with customer deliveries beginning in early 2004. The Sovereign will be powered by two Pratt & Whitney PW306C engines, each with a takeoff thrust of 5686 lb flat-rated to ISA +15°C, enabling a cruising speed of up to 444 kts. Controlled by dual Full Authority Digital Electronic Control (FADEC) systems and using a single-pivot thrust reverser design, the engine has 3000 h HIS and 6000 h TBO maintenance intervals. The company has finalized the design of the aircraft's engine nacelle assembly, which consists of the engine cowling, inlet assembly, throttle quadrant, and thrust reverser

A Parametric Study of Performance Characteristics of Loop Heat Pipes

1999-01-200607/12/1999

A parametric study of performance characteristics of a Loop Heat Pipe (LHP) is presented. A mathematical model, based on the steady-state energy conservation equations, is used. The calculations are performed by varying the operation conditions (heat load, sink and ambient temperatures, and elevation) and the LHP design parameters (working fluid, transport length size, external thermal conductance of the condenser and wick properties). The results are illustrated on LHP performance curves (saturation temperature as a function of applied power). All the results are compared with a baseline configuration to analyze the effects of different parameters. Operating limits due to various constraints such as heat transport limit, capillary pressure limit and the vapor pressure limit are discussed.

Kaya, Tarik, Ku, Jentung

Aircraft Towbar

ARP1915B (Historical)12/01/1997

This SAE Aerospace Recommended Practice (ARP) outlines the basic general design considerations for aircraft towbars.

AGE-3 Aircraft Ground Support Equipment Committee

The Convair Flying Automobile

92156608/01/1992

Goldsworthy, Brandt

Advanced Cooling Systems for Agricultural and Industrial Machines

75118302/01/1975

This paper describes a number of major modifications and alterations which have the potential to improve engine cooling systems for agricultural and industrial machines. Of the passive augmentation schemes studied (packed-beds, gas/solid suspensions, and spray cooling), spray cooling is the only one which has potential for practical application, but only for intermittent use to avoid overdesign of conventional cooling systems. The active augmentation techniques considered (surface scrapers, acoustic vibrations, and electric fields) involve additional system complexity. Acoustic vibrations and electric fields are not effective enough to justify their use in augmentating heat transfer in conventional cores. Recent laboratory tests of the surface scraping technique indicate that this method is very effective for improving heat transfer to air flows. Studies of several new cooling arrangements indicate that direct contact heat exchangers and vaporization and condensation of engine coolant

Bergles, Arthur E., Junkhan, George H., Jensen, Michael K., Hagge, John K.

Propulsion System Design for Maintainability in the Lockheed 1011

69039002/01/1969

The steps involved in design and development of the L-1011 propulsion system, with emphasis on maintenance aspects of the program, are summarized. System requirements, including maintainability and reliability, performance, and noise are reviewed. Major factors leading to determination of the propulsion system configuration are summarized and the rationale for meeting requirements of the various components leading to a well balanced propulsion system is presented. It is shown that the three-spool RB.211 engine satisfies requirements for minimum maintenance of the basic engine. The paper also indicates advantages of an intermediate-length cowl in conjunction with an integral fan duct and reverser and engine accessories mounted externally on the fan case. Finally, certain key design features of the propulsion system are described as they relate to system and component maintainability.

Stroud, John F., Davenport, C. R.

The Plessey Constant Speed Drive/Starter and Its Application to the BAC 1-11 Commercial Transport

67054602/01/1967

Prior to the introduction of the BAC 1–11 aircraft, constant speed generator drives were primarily the hydro-mechanical type; i.e., the engine speed was trimmed by the use of hydraulic devices. The BAC 1–11 has introduced the Plessey CSDS, a pneumatically trimmed unit which assumes the dual role of a CSD and an engine starter. This unit is basically an epicyclic gear train which takes inputs from both the engine and a reversible roots type air motor/blower to drive an A-C generator at a constant speed. This paper will discuss the design, operation, and performance of this unique unit.

Smith, R. L

Body Aerodynamics and Heater Air Flow

66038802/01/1966

The heater air flow rate is a function not only of the heater itself but also of the size and location of the heater system air inlets, the car body air outlets, and the body surface pressure at these inlets and outlets. Favorable pressure conditions generally exist at the typical top cowl heater air inlet; however, the aerodynamics of each particular vehicle should be studied to confirm the existence of these conditions. Little consideration has been given to body air outlet pressure conditions since body leakage paths have generally served as adequate air outlets; but, as body leakage is reduced, specific air outlets must be considered and a knowledge of aerodynamics is essential to the achieving of appropriately sized and appropriately located air outlets.

Shirk, Ricklef W.

Development of Air Conditioning in Beech Airplanes

66020902/01/1966

A general discussion of the problems involved in introducing air conditioning in small executive aircraft. The discussion includes: (1) early studies and hardware for “add on” package units, (2) system selection studies for small pressurized turbine powered aircraft, (3) system design including structural changes required, (4) testing, development and service experience on the Beech King Air cooling system and (5) other applications and possible future development trends.

Clay, L. B.

Airline Experience With Aircraft Engine Lubricating Oils

51015301/01/1951

TAYLOR, HARRY N.

COMPARISON OF USE OF MIXED STRUCTURAL MATERIALS AND FABRIC COVERING TO ALL-METAL CONSTRUCTION FOR PERSONAL AIRCRAFT FROM A MANUFACTURING VIEWPOINT

47015001/01/1947

JAMOUNEAU, WALTER C.

Fuel Injection For Light Aircraft

47018901/01/1947

LANGE, GEORGE M.

THE AIRPLANE ICING PROBLEM and Its Alleviation through Research

46024501/01/1946

FOR the benefit of those who, though interested, have been unable to follow recent developments in ice-prevention equipment, Mr. Jones summarizes the results of research over the past few years. An excellent series of photographs is included to show both the various forms of ice accumulation and the use of thermal equipment to overcome this hazard. The conclusion reached is that properly designed thermal devices properly operated can satisfactorily prevent most icing of airplane surfaces where such prevention is necessary.

JONES, ALUN R.

The INTERCOOLING PROBLEM in AIRPLANE DESIGN

44020701/01/1944

A DISCUSSION of the aircraft-engine charge-air cooling problem is given here from the point of view of the airframe designer. Many of the factors which enter into the selection of the type and capacity of charge-air cooling installations are difficult to subject to quantitative analysis. Among these are problems of simplicity, maintenance, accessibility, and arrangement of the engine installation. In general, however, the difficulty of installation of the charge-air system is out of proportion to the core size. The weight increase due to the system, for instance, is in the neighborhood of five times the weight of the air-to-air intercooler core. The use of a liquid-to-air aftercooler system as opposed to an air-to-air intercooler system shows promise only in applications with liquid-cooled engines where the separation of the ultimate cooling unit from the rest of the installation is a definite arrangement advantage.

DICKINSON, HOLLEY B.

The Use of PETROLEUM PRODUCTS in AIRCRAFT

43015001/01/1943

KLEIN, FRANK D.

CABIN SUPERCHARGING in Scheduled AIRLINE OPERATION

43014201/01/1943

ELLINGER, R. L.

Design of Cowlings for Air-Cooled Aircraft Engines

37019301/01/1937

RECENT work on cowlings for air-cooled engines has been characterized by the correlation of the cooling function of the cowl with the drag-reducing function into a rational design procedure, whereas earlier work was devoted largely to drag reduction and this was a cut-and-try proceeding. The fundamental relations between the pressures and velocities of the external and internal air flows are discussed here in their relation to the quantity of air available for cooling and the effect on drag. Experimental results are outlined, and a design procedure is indicated. It is pointed out that certain factors must be determined by the engine manufacturers in order that a rational design of cowl may be laid out. The shape of the cowling nose is not critical, and the part of the drag that is subject to control is determined by the air flow out the cowl exit. For an efficient cowling and for control of the air flow, the exit is the important part. A procedure is given for designing an efficient

Wood, Donald H.

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