Rotor Damper Contact Biasing for Turbine Vibration

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Solution Overview

Problem

The performance of dampers in gas turbine engines deteriorates over time due to wear, leading to reduced contact force and decreased effectiveness in minimizing vibrations and attenuating rotor blade responses.

Innovation Solution

The design incorporates a damper with an inner band fixed to the rotor mount, a radially extending damper body, and a projection that axially extends between the damper body and the rotor ring, maintaining contact force by utilizing centripetal forces to keep the damper engaged with the rotor even as it wears.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If the damper engages the rotor ring continuously, then vibration attenuation is improved, but contact force decreases over time due to wear

Engineering Contradiction:

Improvevibration attenuation effectivenessVSAvoidcontact force

Core Design Contradiction:

ReliabilityVSForce

Solution Approach 1:

The damper is designed with the ability to dynamically adjust its engagement with the rotor ring. The projection extends axially between the damper body and rotor ring, creating a mechanism where the damper can maintain optimal contact force through controlled engagement and disengagement cycles, preventing the continuous wear that would otherwise reduce contact force over time

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The invention changes the contact parameters by introducing a projection that axially extends between the damper body and rotor ring. This projection modifies the engagement geometry, allowing the system to maintain consistent contact force despite wear by altering how the damper body interfaces with the rotor ring surface

Inventive Principle:

Principle #35Parameter changes

2Ease of manufacture

If the damper structure is simplified, then manufacturing ease is improved, but ability to maintain contact force deteriorates

Engineering Contradiction:

Improvedamper manufacturing simplicityVSAvoidcontact force maintenance

Core Design Contradiction:

Ease of manufactureVSForce

Solution Approach 1:

The damper is segmented into distinct functional components: an inner band fixed to the mount, a radially extending damper body, and a projection extending axially between the body and rotor ring. This segmentation allows each component to be optimized for its specific function while maintaining overall manufacturing simplicity through modular construction

Inventive Principle:

Principle #1Segmentation

Applied Scientific Principles

This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.

Function Achieved in This Case

This configuration maintains the damper's ability to attenuate vibrations and respond to rotor blade responses by ensuring consistent contact between the damper and the rotor, despite wear, thereby enhancing the stability and performance of the gas turbine engine.

Implementation Method 1

maintaining contact force by utilizing centripetal forces to keep the damper engaged with the rotor even as it wears

Methodology Applied

Scientific EffectCentripetal force: Centrifugal Force

Implementation Method 2

the damper's ability to minimize vibrations of the rotor assembly and attenuate rotor blade responses

Methodology Applied

Scientific EffectVibration damping: Damping

Data Source

PatentUS11686202B1Rotor damper with contact biasing feature for turbine engines

Publication Date: 2023.06.27 ROLLS ROYCE NORTH AMERICAN TECHNOLOGIES INC

AI summary

A rotor assembly for a gas turbine engine includes a rotor extending circumferentially about a central axis. The rotor includes a ring that extends around the central axis and a mount that extends axially away from the ring. The ring includes an axially facing engagement surface. A blade extends radially outward from the ring of the rotor. A damper is coupled with the mount of the rotor and engaged with the engagement surface to minimize vibrations of the rotor assembly.