Turbomachine Combustion Chamber Flange Triangular Orifices

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Solution Overview

Problem

Combustion chambers for turbomachines face a trade-off between maximizing air flow area and minimizing pressure drop while maintaining good vibration resistance and circumferential stiffness, which existing rectangular and circular orifices fail to achieve effectively.

Innovation Solution

The combustion chamber features annular flanges with triangular orifices, optimized in shape and arrangement to provide a large air flow area, reduced mass, and enhanced vibration resistance, along with improved circumferential stiffness, achieved through a staggered and imbricated configuration with zig-zag material strips.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Area of moving object

If rectangular orifices are used in flanges, then air flow area is increased and mass is reduced, but vibration resistance deteriorates

Engineering Contradiction:
Improveair flow areaVSAvoidvibration resistance
Core Design Contradiction:
Area of moving objectVSReliability

Solution Approach 1:

The patent applies asymmetry by using triangular orifices instead of symmetric rectangular or circular shapes. The triangular geometry with rounded apexes creates an asymmetric form that optimizes both flow area and structural strength, resolving the contradiction between maximizing air flow and maintaining vibration resistance.

Inventive Principle:
Principle #4Asymmetry

Solution Approach 2:

The patent changes the geometric parameters of the orifices from rectangular to triangular shape, and further optimizes by rounding the apexes. This parameter transformation allows the orifices to achieve both large flow area and good vibration resistance simultaneously, addressing the technical contradiction.

Inventive Principle:
Principle #35Parameter changes

2Reliability

If circular orifices are used in flanges, then vibration resistance is improved, but air flow area is reduced and pressure drop increases

Engineering Contradiction:
Improvevibration resistanceVSAvoidair flow area
Core Design Contradiction:
ReliabilityVSArea of moving object

Solution Approach 1:

The patent moves away from the symmetric circular shape to an asymmetric triangular configuration. This asymmetric design allows the orifices to achieve better flow characteristics with larger effective area while maintaining structural integrity and vibration resistance through the triangular geometry and rounded apexes.

Inventive Principle:
Principle #4Asymmetry

Solution Approach 2:

The patent transforms the orifice geometry from circular to triangular with rounded apexes, optimizing the parameters to simultaneously achieve large air flow area, low pressure drop, and good vibration resistance, thereby resolving the contradiction between flow performance and structural strength.

Inventive Principle:
Principle #35Parameter changes

3Weight of stationary object

If rectangular orifices are used in flanges, then mass is reduced, but circumferential stiffness deteriorates

Engineering Contradiction:
Improveflange massVSAvoidcircumferential stiffness
Core Design Contradiction:
Weight of stationary objectVSStability of the object's composition

Solution Approach 1:

The patent uses asymmetric triangular orifice shapes instead of rectangular configurations. The triangular geometry with rounded apexes and zig-zag arrangement of material strips provides optimized structural distribution that maintains circumferential stiffness while minimizing flange mass.

Inventive Principle:
Principle #4Asymmetry

Solution Approach 2:

The patent introduces dimensional complexity by arranging triangular orifices in a zig-zag pattern and using rounded apexes, transforming the simple rectangular configuration into a multi-dimensional optimized structure that enhances circumferential stiffness without increasing mass.

Inventive Principle:
Principle #17Another dimension (Dimensionality change)

Data Source

PatentUS7568350B2Combustion chamber for a turbomachine
Publication Date: 2009.08.04 SAFRAN AIRCRAFT ENGINES SAS
  • US7568350B2 patent drawing
  • US7568350B2 patent drawing
  • US7568350B2 patent drawing

AI summary

Combustion chamber for a turbomachine, comprising a chamber endwall equipped with fuel injection means and axisymmetric walls connecting the chamber endwall to internal and external flanges for fastening to internal and external casings, these flanges including annular portions pierced by orifices of triangular or approximately triangular shape for the flow of air for cooling downstream components.