• The Korean Journal of Emergency Medical Services
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• v.22 no.3
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• pp.35-45
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• 2018

Purpose: The purpose of this study was to compare laryngoscopic views and ease of use and success of intubation, via the percentage of glottic opening (POGO) scale when using the Miller blade and Macintosh blade in paraglossal approach. Methods: Forty intern doctors were randomized for laryngoscopy to be performed in a crossover manner. They performed endotracheal intubation with Miller blade and Macintosh blade in two airway scenarios: normal airway and difficult airway with edema. We observed the rate of successful intubation, time required for visualizing the glottis, time to complete endotracheal intubation, ease of intubation, and the POGO scale. Results: In the normal airway, there was no difference in intubation between the two endoscopes. In the difficult airway, the time for visualizing the glottis (7.80 versus 10.24 sec; p=.006), the time to tube passage (19.38 versus 23.03 sec; p=.038) and the time to complete endotracheal intubation (21.84 versus 28.54 sec; p=.022) with Miller blade was shorter than with Macintosh blade. The POGO scale(%) of the Miller blade was higher than that of the Macintosh blade's (62.25 versus 56.32; p=.030). Conclusion: Compared to the Macintosh blade, Miller blade provided better visualization of the glottis and POGO scale, and faster time to completion of endotracheal intubation.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.18 no.1
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• pp.1-10
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• 2010

Structures under high temperature may have creep behavior and fatigue behavior. Durability study of the structures need the damage analysis with the creep-fatigue effects. In this paper, the damage analysis is studied for a turbine blade in the turbopump for a liquid rocket engine which is operated under high temperature condition. First of all, the load cycle is required for defining the operational characteristics of turbopump. The thermal stress analysis is done for a turbine blade of the turbopump. The stress analysis results are used to judge damage due to the creep and the fatigue. The strain-life method with miner rule is used for fatigue damage analysis. The Larson-Miller parameter master curve and robinson rule are used for the creep damage analysis. The linear damage summation method is used to consider creep-fatigue effects of turbopump turbine. Finally, the analysis results for fatigue and the influence are compared to figure out the damage phenomenon of the turbopump turbine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.382-386
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• 2009

The life of a component decreases when it was exposed at the extreme condition. A turbine blade of a turbopump used for a liquid rocket engine is operated under the environment of high temperature and pressure, and experienced high centrifugal force. Thus the durability of the turbopump operated under the these conditions become lower than expected because of the severe fatigue and creep influence. The damage of the turbine being considered the fatigue and the creep influence is estimated to ensure the durability of turbopump turbine. ABAQUS/CAE and MSC.Fatigue are used for the fatigue analysis, and Larson-Miller parameter and robinson's rule are used for the creep analysis. In this paper, comparison and analysis of the fatigue and the creep influence were performed to ensure the life expectancy of turbopump turbine.

• Analytical Science and Technology
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• v.21 no.2
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• pp.148-157
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• 2008

To describe the lifetime prediction of gas turbine core parts serviced in some ten thousands rpms at over $1,000^{\circ}C$, the Larson-Miller Creep Curves, which are formed by creep rupture tests as the destructive experiment with parameters of stress and temperature, are used often, but not exact and reliable with errors of over some tens. On the other hand, this study shows a non-destructive method with increased accuracy and reliability. The SEM and TEM specimens were extracted by replica after polishing the local airfoil and root surfaces of the first stage scraped blade (bucket), serviced for 18,000 hours at $1,280^{\circ}C$ in Gas Turbines of Boryong. The observed TEM and SEM precipitates were digitalized for calculation of the average size. Here we could find the precipitate size grown from $0.45{\mu}m$ to $0.6{\mu}m$ during service and the grown precipitates to be still sound. From these results we could conclude that the scraped balde can be used for ten thous and hours additionally and for twenty thousand hours by additional heat treatments on the scraped blade.