Ceramic Matrix Composite Combustor Dome for Gas Turbine Engines
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engines face challenges in accommodating the mechanical properties of ceramic matrix composite (CMC) materials, particularly with thermal expansion differences, which can disrupt combustion gas flow and complicate component mounting without requiring additional metal parts.
Innovation Solution
A combustor assembly using a ceramic matrix composite material for both the liner and dome, with integrally formed components and direct attachment of fuel-air injector hardware to the dome, eliminating the need for additional metal components and ensuring smooth gas flow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If traditional metal materials are used for the combustor dome and liner, then mechanical properties and ease of manufacture are improved, but thermal expansion differences disrupt combustion gas flow and aerodynamic performance deteriorates
Solution Approach 1:
The patent applies homogeneity by making both the combustor dome and liner components from the same CMC material, ensuring uniform thermal expansion characteristics throughout the combustor assembly. This eliminates the thermal expansion mismatch between different materials that previously disrupted combustion gas flow, creating a homogeneous thermal response across all combustor components.
Solution Approach 2:
The patent utilizes CMC composite materials for both the dome and liner, replacing traditional metal materials. This composite material approach provides the necessary mechanical properties while enabling uniform thermal expansion behavior, resolving the contradiction between mechanical performance and aerodynamic flow quality.
2Ease of manufacture
If additional metal attachment components are used to mount fuel-air injectors to CMC dome, then ease of manufacture is improved, but device complexity increases and aerodynamic performance deteriorates
Solution Approach 1:
The patent merges the dome structure with the fuel-air injector mounting function by integrating attachment features directly into the CMC dome component. This eliminates the need for separate metal attachment components, reducing device complexity while maintaining ease of manufacture through direct integration of mounting capabilities.
Solution Approach 2:
The CMC dome is designed with multi-functionality, serving both as the structural combustor component and as the mounting substrate for fuel-air injectors. By incorporating attachment features directly into the dome, the component performs multiple functions without requiring additional specialized parts, reducing overall device complexity.
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
The solution allows for efficient operation of gas turbine engines using CMC materials without disrupting combustion gas flow, enabling uniform thermal expansion and reducing the complexity of component mounting, thus enhancing the engine's performance and reliability.
Implementation Method 1
CMC materials have different coefficients of thermal expansion than the traditional metal materials
Data Source
AI summary
A combustor assembly for a gas turbine engine is includes a liner and a combustor dome formed of a ceramic matrix composite material. The combustor dome and liner together define at least in part a combustion chamber. The combustor dome extends along a circumferential direction and defines one or more openings, the combustor dome is configured to receive one or more fuel-air injector hardware assemblies in or through the one or more openings.