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Insight into Damping Sources in Turbines

Grzegorz Moneta

Grzegorz Moneta

Łukasiewicz Research Network, Institute of AviationWarsaw, Poland
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Moneta, Grzegorz
  
28 nov 2023
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Categoría del artículo: research article
Publicado en línea: 28 nov 2023
Páginas: 69 - 82
DOI: https://doi.org/10.2478/fas-2022-0006
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© 2022 Grzegorz Moneta, published by Sciendo
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Figure 1.

Turbine blade loss caused by HCF (DFS, 2014). HCF, high cycle fatigue.
Turbine blade loss caused by HCF (DFS, 2014). HCF, high cycle fatigue.

Figure 2.

Scheme of blade fatigue assessment using the Haigh diagram.
Scheme of blade fatigue assessment using the Haigh diagram.

Figure 3.

Damping components in turbine blading.
Damping components in turbine blading.

Figure 4.

An example of a hysteresis loop with cyclic deformation of the material.
An example of a hysteresis loop with cyclic deformation of the material.

Figure 5.

Example of temperature and vibration frequency influence on material damping (Braun et al., 2002).
Example of temperature and vibration frequency influence on material damping (Braun et al., 2002).

Figure 6.

Influence of stress amplitude on material damping of selected alloys at room temperature (Szmid, 1962; Szwedowicz, 2012).
Influence of stress amplitude on material damping of selected alloys at room temperature (Szmid, 1962; Szwedowicz, 2012).

Figure 7.

Friction models: a) rigid contact, b) macro-slip, c) micro-slip.
Friction models: a) rigid contact, b) macro-slip, c) micro-slip.

Figure 8.

Influence of load and stress amplitude on friction damping in fir-tree root (Klepacki, 1975).
Influence of load and stress amplitude on friction damping in fir-tree root (Klepacki, 1975).

Figure 9.

Isochromatic pattern in two different pairs of fir-tree locks (Klepacki, 1975).
Isochromatic pattern in two different pairs of fir-tree locks (Klepacki, 1975).

Figure 10.

Stress amplitudes in the blade with and without friction dampers as a function of rotational speed (Klepacki, 1978).
Stress amplitudes in the blade with and without friction dampers as a function of rotational speed (Klepacki, 1978).

Comparison of the aerodynamic damping ratio of turbine blades

Object Aerodynamic damping ratio ζa [-] Source
SO-3 turbine blades (free-standing) 0.14% (calculated) Formulas (Eqs. 1 and 2)
High pressure turbine blades of Honeywell TFE 731-2 engine (free-standing) 0.14%–0.26% (±0.11%) Kielb & Abhari, 2001
Steam turbine blades (free-standing) 0.21%–0.40% Brown, 1981

Comparison of the impact of friction dampers on blade vibrations_

Object Amplitude reduction (%) Source
SO-3 turbine (free-standing blades, baseline under-platform dampers) -62.0 Klepacki, 1975
SO-3 turbine (free-standing blades, optimized under-platform dampers) -74.0 Moneta, 2019
Axial compressor (free-standing blades, roller under-platform dampers) -80.0 Hanson, 1956
Volvo RM6/RM8 turbine (freestanding blades, under-platform dampers) -80.0 Csaba, 1997
Steam turbine (last stage blades coupled by damping bolts) -83.3 Szwedowicz, 2008
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