Blade design aspects

Scherer, Roger Lima

doi:10.1016/s0960-1481(98)00516-3

Cited by 8 publications

(3 citation statements)

References 0 publications

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“…Its main drawbacks are the use of slip rings and protection in case of grid disturbances [6]. The control can be done (a) by controlling the voltage applied to the rotor circuits, (b) by adjusting the pitch angle of the turbine blades-angle of incidence of the blade and the wind direction-, and (c) by designing aerodynamically the turbine blades to stall when the wind speed exceeds its limit [7].…”

Section: Introductionmentioning

confidence: 99%

Dynamic modeling of wind power generation

Pulgar-Painemal

Sauer

2009

41st North American Power Symposium

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This paper presents a dynamic model appropriate for power system analysis. This article shows modeling assumptions, derivation of a third order model for a doubly-fed induction generator and its controller models. Due to the detail level, it can be used as a tutorial for students and engineers that are new in this area. A four-bus system with one synchronous machine and one wind turbine is used to perform a small signal stability analysis. No considerable difference is observed between the modal behavior of our test system and a small system with just one synchronous generator.

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Section: Introductionmentioning

confidence: 99%

Dynamic modeling of wind power generation

Pulgar-Painemal

Sauer

2009

41st North American Power Symposium

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“…When a compressor operates at rotational speeds well below the design value, the air density in the last few stages is very low, the axial flow velocity becomes excessive, and the blades stall [1][2][3]. Stalls may lead to aerodynamically induced vibrations resulting in fatigue failures and total engine destruction [4].…”

Section: Introductionmentioning

confidence: 99%

Failure of the J79 Engine Compressor Blade Due to Stall

Song¹,

Kim²,

Hwang³

2007

J Fail. Anal. and Preven.

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The fractured and damaged compressor rotor blades of a J79 engine have been examined. Optical, stereoscopic, microhardness testing, and SEM examinations were carried out to find out the causes of the fracture. The material of the blades was STS403 and blades were used without coating. From the 15th through the 17th compressor stages the rotor blades, stator vanes, combustion, and turbine sections were damaged. The fractured surface of the 17th blade show multiple origins, secondary cracking in the blade's convex surface, and extensive propagation before separation and rougher surfaces. The metallographic analysis of the microstructure suggested work hardening. Based on the results, the cause of the fractured blade was highamplitude fatigue, due to severe stall. After normal engine usage of 5 months, the blade fractured and blade fragments hit the other compressor blades, stators, and casing, and caused damage in both combustion and turbine sections.

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“…The reliable, safe and economic design of a blade turbine is a fundamental aspect in the future of this technology [7]. A model that has been widely used-extracted from the Glauert Blade Element Momentum theory [8]-has been adapted to the presented purpose.…”

Section: Introductionmentioning

confidence: 99%