Gas Turbine Combustor Liner Projections for Cooling
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Solution Overview
Problem
Existing combustor designs for gas turbine engines fail to provide adequate cooling performance, as they either obstruct compressed air flow or rely on inefficient film cooling methods, leading to insufficient heat transfer from high-temperature combustion gases to the liner.
Innovation Solution
A combustor design featuring a liner with projections and cooling holes that promote turbulent airflow and directed convection, where cooling holes are strategically positioned to maximize heat transfer and airflow deceleration, forming a heat shielding layer on the inner surface to reduce temperature rise.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling holes are formed in the liner to introduce compressed air into the combustion chamber, then film cooling of the liner inner surface is achieved, but the cooling performance is insufficient
Solution Approach 1:
The liner is divided into different regions with distinct cooling mechanisms: the projection region features protrusions that generate turbulent flow and enhance convection cooling on the outer surface, while the inner surface utilizes film cooling through strategically positioned cooling holes. This local differentiation of cooling methods optimizes heat transfer efficiency at each surface.
Solution Approach 2:
The invention combines two cooling mechanisms (convection cooling via turbulent flow generation and film cooling) into a single integrated liner structure. The projections on the outer surface generate turbulence to enhance convection cooling, while cooling holes provide film cooling on the inner surface, creating a dual-mode cooling system that significantly improves overall cooling performance.
2Temperature
If projections are provided on the liner outer surface to generate turbulent flow, then convection cooling is enhanced, but the device complexity increases
Solution Approach 1:
The liner incorporates cooling holes that allow compressed air to pass through from the outer surface to the inner surface. These holes create a porous-like structure that enables film cooling, where the injected air forms a protective layer along the inner surface, reducing heat transfer from the combustion gases to the liner.
Solution Approach 2:
The cooling holes are configured with a specific orientation where the outlet on the inner surface is positioned downstream relative to the inlet on the outer surface. This three-dimensional arrangement of the cooling holes creates an angled flow path that optimizes film formation and heat shielding effectiveness.
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 design effectively enhances cooling performance by promoting turbulent airflow and stabilizing compressed air flow, leading to improved heat transfer and reduced temperature rise of the combustor liner, thereby improving the overall cooling efficiency of the gas turbine engine.
Implementation Method 1
the projections obstruct the flow of the compressed air flowing through the compressed air chamber so that a turbulent flow of compressed air is generated around the projections
Implementation Method 2
This causes convection of compressed air at a relatively low temperature causing the liner at a relatively high temperature to be cooled
Implementation Method 3
a technology based on film cooling of the inner surface of the liner by conducting compressed air into the combustion chamber via cooling holes formed in the liner
Implementation Method 4
This film of air serves as a heat insulating layer
Implementation Method 5
since at least a part of the cooling holes are provided in the projection region, the compressed air is decelerated in the flow direction thereof around the projections so that the compressed air is more actively introduced into the cooling holes
Data Source
AI summary
The liner of a combustor (100) for a gas turbine engine is provided with a projection region (111) provided with a plurality of projections (110) each projecting toward the compressed air chamber (56) from the liner outer surface and having a vertical wall portion (114) extending substantially orthogonally to a flow direction of compressed air flowing in the compressed air chamber, and a plurality of cooling holes (118) passed through the liner from the liner outer surface to the liner inner surface such that an end of each cooling hole on a side of the compressed air chamber is more downstream than an end of the cooling hole on a side of the combustion chamber (52) with respect to the flow direction of the compressed air in the compressed air chamber, at least a part of the cooling holes being formed in the projection region.