The Effect of Compressor Rotor Tip Crops on Turboshaft Engine Performance

Frith, Peter

doi:10.1115/92-gt-083

Cited by 8 publications

(4 citation statements)

References 5 publications

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“…Changes in surface quality and airfoil geometry reduce efficiency and work capability of the stage. Increased clearances reduce surge margin, reduce the efficiency, cause a reduction in stage work, and reduce the compressor flow capacity (Kurz and Brun, 2001;Spakovszky et al, 1999;Graf et al, 1998;Smith and Cumpsty, 1984;Frith, 1992).…”

Section: Degradation Of Componentsmentioning

confidence: 99%

Degradation of gas turbine performance in natural gas service

Kurz¹,

Brun

2009

Journal of Natural Gas Science and Engineering

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Section: Degradation Of Componentsmentioning

confidence: 99%

Degradation of gas turbine performance in natural gas service

Kurz¹,

Brun

2009

Journal of Natural Gas Science and Engineering

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“…This is mainly due to the leakage flow from pressure surface to the suction surface through the tip clearance area. Frith [180] Compressor A 3% tip clearance increase on the axial compressor stages decreases flow capacity by 4.6% and drops the pressure ratio by 3%, and decrease in compressor efficiency by 2.5%. Melcher and Kypuros [181] Turbine A 0.25mm change in turbine tip clearance may cause up to 10°C engine exhaust gas temperature and decrease turbine efficiency up to 1.3% Radtke and Dibelius [182] Turbine…”

Section: F) Thermal Distortionmentioning

confidence: 99%

Performance-based health monitoring, diagnostics and prognostics for condition-based maintenance of gas turbines: A review

Tahan¹,

Tsoutsanis

Muhammad³

et al. 2017

Applied Energy

340

158

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With the privatization and intense competition that characterize the volatile energy sector, the gas turbine industry currently faces new challenges of increasing operational flexibility, reducing operating costs, improving reliability and availability while mitigating the environmental impact. In this complex, changing sector, the gas turbine community could address a set of these challenges by further development of high fidelity, more accurate and computationally efficient engine health assessment, diagnostic and prognostic systems. Recent studies have shown that engine gas-path performance monitoring still remains the cornerstone for making informed decisions in operation and maintenance of gas turbines. This paper offers a systematic review of recently developed engine performance monitoring, diagnostic and prognostic techniques. The inception of performance monitoring and its evolution over time, techniques used to establish a highquality dataset using engine model performance adaptation, and effects of computationally intelligent techniques on promoting the implementation of engine fault diagnosis are reviewed. Moreover, recent developments in prognostics techniques designed to enhance the maintenance decision-making scheme and main causes of gas turbine performance deterioration are discussed to facilitate the fault identification module. The article aims to organize, evaluate and identify patterns and trends in the literature as well as recognize research gaps and recommend new research areas in the field of gas turbine performance-based monitoring. The presented insightful concepts provide experts, students or novice researchers and decision-makers working in the area of gas turbine engines with the state of the art for performance-based condition monitoring.

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“…Meanwhile, a slight surge of blades will occur, which will affect the engine's stability. 4 A simulation result showed that compared with configuration 1, which has a small tip clearance of multistage high-pressure compressor, configuration 2, which has a large tip clearance of multistage high-pressure compressor, causes the stable operating range to be reduced by 40%, and the efficiency and pressure ratio are also decreased by 1.5% and 2%, respectively. 5 In addition, the blade tip-clearance changes have a great impact on the rate of fuel consumption.…”

Section: Introductionmentioning

confidence: 99%

A review of blade tip clearance–measuring technologies for gas turbine engines

Shen

et al. 2020

Measurement and Control

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Blade tip clearance is one of the important parameters affecting the performance, safety and stability of a gas turbine engine. However, it is difficult to measure the tip clearance in real time and accurately during the development and test process of an engine. In order to promote the development of tip clearance–measuring technology and the optimal design of the gas turbine engine, some typical measuring methods of tip clearance and a novel measuring method based on AC discharge are introduced. In this article, the significance for measuring tip clearance of an engine is illustrated first. Then, operating principles, characteristics and developments of those typical measurement approaches are introduced. After that, these methods are analyzed, and the particular characteristic of each measuring approach is summarized.

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The Effect of Compressor Rotor Tip Crops on Turboshaft Engine Performance

Cited by 8 publications

References 5 publications

Degradation of gas turbine performance in natural gas service

Degradation of gas turbine performance in natural gas service

Performance-based health monitoring, diagnostics and prognostics for condition-based maintenance of gas turbines: A review

A review of blade tip clearance–measuring technologies for gas turbine engines

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