Annular Seal Grooves Prevent Extrusion in High-Pressure Compressors

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Solution Overview

Problem

Traditional O-rings in high-pressure compressors experience increased failure rates due to radial expansion of the casing and fluid absorption, leading to extrusion and blistering under high pressure conditions.

Innovation Solution

An annular seal with a generally rectangular cross-section, featuring an outer radial surface with annular grooves and slots, and axial sidewalls, configured to maintain a low-pressure environment on one side and a high-pressure environment on the other, is mounted between the compressor bundle and housing to provide effective sealing.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If O-rings are used to seal the compressor bundle, then sealing is achieved, but the O-rings absorb fluid at high pressure and blister or explode when pressure is reduced

Engineering Contradiction:
Improvesealing performanceVSAvoidfluid absorption and blistering
Core Design Contradiction:
ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The fluid absorption problem is mitigated by segmenting the seal into multiple smaller O-rings rather than one large O-ring. Each smaller O-ring absorbs less fluid, reducing the cumulative blisting risk while maintaining sealing effectiveness across the entire circumference.

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

Backup rings are introduced as intermediary elements between the O-rings and the expansion gap. These backup rings act as barriers that prevent fluid-saturated O-rings from contacting each other and failing, allowing the system to tolerate fluid absorption without catastrophic failure.

Inventive Principle:
Principle #24Intermediary (Mediator)

2Stress or pressure

If the compressor casing expands radially under high pressure, then the casing accommodates pressure, but the gap between compressor bundle and casing increases promoting O-ring extrusion

Engineering Contradiction:
Improvehigh pressure containmentVSAvoidO-ring extrusion
Core Design Contradiction:
Stress or pressureVSObject-affected harmful factors

Solution Approach 1:

The groove configuration segments the potential extrusion path into isolated sections. Each O-ring is confined to its own groove, so even when the casing expands and creates gaps, the O-rings cannot extrude into the expansion space because the grooves act as physical barriers containing each seal element independently.

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

The design accepts that casing expansion will create gaps, but converts this potentially harmful effect into a benign condition by providing backup rings that fill the expansion gap. The gap that would normally cause extrusion is instead filled with inert backup ring material that prevents O-ring contact and failure.

Inventive Principle:
Principle #22Blessing in disguise (Convert harm into benefit)

Data Source

PatentEP3019778B1Compressor with annular seal
Publication Date: 2019.10.30 DRESSER RAND CO
  • EP3019778B1 patent drawingFigure 1A
  • EP3019778B1 patent drawingFigure 1B
  • EP3019778B1 patent drawingFigure 2~3

AI summary

An annular seal is provided for use in a turbomachine. The annular seal may form a generally rectangular cross-section and may include an outer radial surface forming an outer sealing surface and defining at least one annular groove and a plurality of slots spaced circumferentially about the outer radial surface. Each slot may have an end terminating in the at least one annular groove. The annular seal may also include a first axial sidewall forming a sidewall sealing surface and a recessed portion and a second axial sidewall opposing the first axial sidewall. At least one annular groove and the plurality of slots may be configured to maintain a low pressure environment across at least a portion of the outer radial surface. The second axial sidewall, the recessed portion, and the inner radial surface may be configured to maintain a high pressure environment there across during operation of the turbomachine.