Curved Interface Passage for Gas Turbine Combustor Liner Panels

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

The combustor section of gas turbine engines faces challenges in durability and cooling efficiency due to thermally challenging environments and adverse local aerodynamics, particularly at interfaces where forward and aft panels merge, leading to steps, dead regions, and cooling challenges.

Innovation Solution

The implementation of a curved interface passage in the combustor wall assembly, formed by the aft and forward circumferential rails, directs leakage flow in a parabolic path parallel to the hot side of the liner panels, promoting film attachment and enhancing cooling effectiveness while shielding the support shell from direct heat flow.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of manufacture

If straight edges and linear profiles are used for liner panels, then manufacturing and assembly are simplified, but adverse local aerodynamics and dead regions occur at panel interfaces

Engineering Contradiction:

Improvepanel fabrication simplicityVSAvoidadverse local aerodynamics

Core Design Contradiction:

Ease of manufactureVSObject-affected harmful factors

Solution Approach 1:

The patent applies curvature to the interface passage by forming it with a curved radius rather than straight edges. This curved geometry eliminates dead regions and improves airflow patterns at the panel interfaces, resolving the adverse local aerodynamics while maintaining manufacturing feasibility through standard curved machining operations.

Inventive Principle:

Principle #14Spheroidality (Curvature)

2Reliability

If panels terminate where combustor geometry transitions, then durability is improved, but steps and dead regions occur at panel interfaces

Engineering Contradiction:

Improvecombustor durabilityVSAvoiddead regions

Core Design Contradiction:

ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The curved interface passage eliminates dead regions at panel termination points by providing continuous curved surfaces that guide airflow smoothly. This maintains the durability benefits of panel termination at geometry transitions while eliminating the harmful dead regions that would otherwise form.

Inventive Principle:

Principle #14Spheroidality (Curvature)

Solution Approach 2:

The invention uses fluid flow (cooling air) dynamics to resolve the contradiction by designing the interface passage curvature to optimize airflow patterns. The curved geometry leverages pneumatic principles to prevent flow separation and dead region formation, improving both durability and aerodynamic performance.

Inventive Principle:

Principle #29Pneumatics and hydraulics

3Reliability

If cooling airflow is provided to meet service life requirements, then durability is improved, but adverse aerodynamics reduce cooling effectiveness

Engineering Contradiction:

Improveservice lifeVSAvoidadverse local aerodynamics

Core Design Contradiction:

ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The curved interface passage improves cooling effectiveness by eliminating adverse aerodynamic features such as flow separation and dead regions. This allows cooling airflow to follow smooth curved paths along the liner panels, enhancing heat transfer efficiency while maintaining the service life benefits of adequate cooling.

Inventive Principle:

Principle #14Spheroidality (Curvature)

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 improves combustor durability and operational life by enhancing film cooling attachment and reducing heat exposure on support shells, thereby improving cooling efficiency and reducing adverse aerodynamic effects.

Implementation Method 1

directs leakage flow in a parabolic path parallel to the hot side of the liner panels

Methodology Applied

Scientific EffectParabolic flow path:

Implementation Method 2

promoting film attachment and enhancing cooling effectiveness

Methodology Applied

Scientific EffectFilm attachment: Coanda Effect

Implementation Method 3

shielding the support shell from direct heat flow

Methodology Applied

Scientific EffectThermal shielding: Thermal Insulation

Implementation Method 4

enhancing cooling effectiveness while shielding the support shell from direct heat flow

Methodology Applied

Scientific EffectFilm cooling: Convection

Data Source

PatentEP3892920B1Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor

Publication Date: 2024.09.04 RTX CORP

Figure 1
Figure 2
Figure 3

AI summary

A combustor (56) for a gas turbine engine (20) includes a support shell (68,70); a first liner panel (72) mounted to the support shell (68,70) via a multiple of studs (100), the first liner panel (72) including a first rail (124a) that extends from a cold side (110) of the first liner panel (72) such that the rail (124a) is non-perpendicular to the cold side (110) and includes a concave surface to at least partially form a curved interface passage (150); and a second liner panel (74) mounted to the support shell (68,70) via a multiple of studs (100), the second liner panel (72) including a second rail (122b) that extends from a cold side (110) of the second liner panel (74) and includes a convex surface to at least partially form the curved interface passage (150).