Understanding the relationship between design margins and trade-offs

To achieve an objective designers often need to make trade-offs between multiple parameters. In incremental design or during the design process an additional objective is often to minimise the changes they need to make to meet the objective. This is in particular an issue for systems with product platforms, over individual components are over-designed. This paper argues that designers can think about this problem in terms of the margins on the objective parameters as well as the parameters that are traded-off. This is illustrated with the case study of an engineering cooling system

Energy Efficient Engine Program Advanced Turbofan Nacelle Definition Study

Advanced, low drag, nacelle configurations were defined for some of the more promising propulsion systems identified in the earlier Benefit/Cost Study, to assess the benefits associated with these advanced technology nacelles and formulate programs for developing these nacelles and low volume thrust reversers/spoilers to a state of technology readiness in the early 1990's. The study results established the design feasibility of advanced technology, slim line nacelles applicable to advanced technology, high bypass ratio turbofan engines. Design feasibility was also established for two low volume thrust reverse/spoiler concepts that meet or exceed the required effectiveness for these engines. These nacelle and thrust reverse/spoiler designs were shown to be applicable in engines with takeoff thrust sizes ranging from 24,000 to 60,000 pounds. The reduced weight, drag, and cost of the advanced technology nacelle installations relative to current technology nacelles offer a mission fuel burn savings ranging from 3.0 to 4.5 percent and direct operating cost plus interest improvements from 1.6 to 2.2 percent

Optimization of Heat Exchanger Design Parameters for Hydrocarbon Refrigerant Systems

Hydrocarbon refrigerants (HC's) are one alternative to hydrofluorocarbons (HFC???s) since they have zero ozone depletion potential and negligible global warming potential. However, due to their flammable nature, the amount of refrigerant used in systems is regulated for safety reasons. This report presents simulation results for a 3-ton R290 (propane) air-conditioning system, and identifies the optimum heat-exchanger geometries that would minimize system charge while trying to retain the same system efficiency. An existing R410A microchannel system simulation served as the base case, and then the geometries were optimized for the R290 system, and the results were compared to the base case. The model was then analyzed for the off-design conditions, and the conclusions presented. The optimal condenser geometry tended to have smaller port diameter and core depth with thicker webs between the ports. Also, the fins tended to be taller, thinner and more densely packed. Similar results were noted for the evaporator geometry. The optimal design reduced the combined heat exchanger charge by more than a factor of 5. The system efficiency was reduced by 3% in the process, but the loss could be recovered because the pressure drop was low enough to permit increasing the air-flow rates. The off-design behavior of the R290 microchannel system is very different from a traditional R410A round-tube plate-fin system. Typically with the increase in ambient temperature, charge from the evaporator and the liquid line moves to the condenser. In the R290 system, because of the oil/refrigerant solubility characteristics, charge from the compressor sump also moves to the condenser. In the microchannel systems, the heat exchangers account for only 20% of the system charge as opposed to 70% in the tube fin systems. At higher ambient temperatures, the additional charge flowing from the other components, provides the condenser with the additional ~7% charge it needs at hot ambient conditions. However, due to the small internal volume of the heat exchangers in microchannel systems, an additional 60% charge flows into the condenser, resulting in high values of subcooling, thus reducing system efficiency. One solution to this problem would be to install a receiver at the outlet from the condenser, to retain high levels of efficiency across a wide range of operating conditions.Air Conditioning and Refrigeration Project 14

NASA. Langley Research Center dry powder towpreg system

Dry powder polymer impregnated carbon fiber tows were produced for preform weaving and composite materials molding applications. In the process, fluidized powder is deposited on spread tow bundles and melted on the fibers by radiant heating to adhere the polymer to the fiber. Unit design theory and operating correlations were developed to provide the basis for scale up of the process to commercial operation. Special features of the operation are the pneumatic tow spreader, fluidized bed, resin feeder, and quality control system. Bench scale experiments, at tow speeds up to 50 cm/sec, demonstrated that process variables can be controlled to produce weavable LARC-TPI carbon fiber towpreg. The towpreg made by the dry powder process was formed into unidirectional fiber moldings and was woven and molded into preform material of good quality

Jet noise from co-axial nozzles over a wide range of geometric and flow parameters

Free field pure jet noise data were taken for a large range of coaxial nozzle configurations. The core nozzles were circular (1 to 4 in. diameter) and plug types. The fan to core area ratio varied from 0.7 to 43.5, while the velocity ratio typically varied from 0 to 1. For most cases the two nozzles were coplanar but large axial extensions of either nozzle were also tested. Correlation of the data resulted in a simple procedure for estimating ambient temperature subsonic coaxial jet noise spectra over a wide range of geometric and flow parameters

The 0.1m subsonic cryogenic tunnel at the University of Southampton

The design and performance of a low speed one atmosphere cryogenic wind tunnel is described. The tunnel is fan driven and operates over the temperature range 305K to 77K at Mach numbers up to 0.28. It is cooled by the injection and evaporation of liquid nitrogen in the circuit, and the usual test gas is nitrogen. The tunnel has a square test section 0.1m across and was built to allow, at low costs, the development of testing techniques and the development of instrumentation for use in cryogenic tunnels, and to exploit in general instrumentation work the unusuallly wide range of unit Reynolds number available in such tunnels. The tunnel was first used in the development of surface flow visualization techniques for use at cryogenic temperatures

A study of electric motors for use in liquid and gaseous helium Engineering report no. 3530

Electric motor design and operation in liquid and gaseous helium environment

Study of fuel systems for LH2-fueled subsonic transport aircraft, volume 1

Several engine concepts examined to determine a preferred design which most effectively exploits the characteristics of hydrogen fuel in aircraft tanks received major emphasis. Many candidate designs of tank structure and cryogenic insulation systems were evaluated. Designs of all major elements of the aircraft fuel system including pumps, lines, valves, regulators, and heat exchangers received attention. Selected designs of boost pumps to be mounted in the LH2 tanks, and of a high pressure pump to be mounted on the engine were defined. A final design of LH2-fueled transport aircraft was established which incorporates a preferred design of fuel system. That aircraft was then compared with a conventionally fueled counterpart designed to equivalent technology standards

Design sensitivity analysis of using various flow boiling correlations for a direct evaporator in high-temperature waste heat recovery ORCs

High-temperature waste heat (250°C-400°C) sources being created by industrial operations such as metallurgical industry, incinerators, combustion engines, annealing furnaces, drying, baking, cement production etc. are being utilized in Organic Rankine cycle (ORC) waste heat recovery systems. Alongside indirect ORC evaporators having intermediate heat carrier loops, ORC waste heat recovery can also be done through a direct evaporator (e.g. tube bundles) applied on a heat source. In an evaporator design problem, the accuracy of the design method has a significant impact on the end result. In that manner, for revealing the design accuracy error margin of using various flow boiling heat transfer methods, a design sensitivity analysis is performed by means of using 13 different flow boiling heat transfer correlations. All correlations are implemented separately into an iterative evaporator calculation and the resulting sizing solutions are compared for a representative high-temperature waste heat recovery evaporator case. The volumetric flow rate of the waste heat is 80000 Nm³/h and the inlet temperature is 375°C. The considered working fluid is cyclopentane and the deduced optimal evaporation temperature (OET) is 227°C. The minimum corresponding total transferred heat in the evaporator is at least 3,5 MW in all calculations