A chambered porous damper for rotor vibration control: Part 2. Imbalance response and blade loss simulation

Journal Article · Thu Apr 01 00:00:00 EST 1993 · Journal of Engineering for Gas Turbines and Power; (United States)

DOI:https://doi.org/10.1115/1.2906718· OSTI ID:6400317

Walton, J; Martin, M ^[1]

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1. Mechanical Technology Inc., Latham, NY (United States)

In this paper, results of experimental rotordynamic evaluations of a novel, high load chambered porous damper design are presented. The chambered porous damper concept was evaluated for gas turbine engine application since this concept avoids the nonlinearities associated with high-eccentricity operation of conventional squeeze film dampers. The rotordynamic testing was conducted under large steady-state imbalance and simulated transient blade-loss conditions for up to 0.254 mm (0.01 in.) mass c.g offset or 180 g-cm (2.5 oz-in.) imbalance. The chambered porous damper demonstrated that the steady-state imbalance and simulated blade-loss transient response of a flexible rotor operating above its first bending critical speed could be readily controlled. Rotor system imbalance sensitivity and logarithmic decrement are presented showing the characteristics of the system with the damper installed. The ability to accommodate high steady-state and transient imbalance conditions makes this damper well suited to a wide range of rotating machinery, including aircraft gas turbine engines.

• OSTI ID: 6400317
• Journal Information: Journal of Engineering for Gas Turbines and Power; (United States), Vol. 115:2; ISSN 0742-4795
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
GAS TURBINE ENGINES
MECHANICAL TESTS
MECHANICAL VIBRATIONS
DAMPING
EXPERIMENTAL DATA
MOMENT OF INERTIA
TURBINE BLADES
VISCOUS FLOW
DATA
ENGINES
FLUID FLOW
HEAT ENGINES
INFORMATION
INTERNAL COMBUSTION ENGINES
MATERIALS TESTING
NUMERICAL DATA
TESTING
330103* - Internal Combustion Engines- Turbine