Two-Stage Gas Turbine Combustor with Offset Fuel Injection
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Solution Overview
Problem
Two-stage combustors in gas turbine engines face challenges in achieving a proper temperature profile and durability due to their complex geometry, which complicates dynamic range management and pilot stage operation.
Innovation Solution
A combustor design featuring an inner and outer annular liner wall forming a combustion chamber with distinct fuel injection stages, an intermediate wall, and a lobed mixer wall for efficient fuel mixing, allowing for separate pilot and main combustion stages with radially and circumferentially offset fuel injection bores.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a two-stage combustor with complex geometry is used to enable pilot and main combustion stages, then the engine can operate at low power settings and prevent flame extinction, but the dynamic range management becomes more difficult and temperature profile control is compromised
Solution Approach 1:
The combustor is divided into two distinct combustion stages (pilot stage and main stage) with separate fuel injection systems. The pilot stage uses a first fuel injection system with bores in the first dome wall, while the main stage uses a second fuel injection system with bores in the second dome wall. This segmentation allows independent control of each stage, enabling the engine to operate efficiently across a wide power range while maintaining manageable complexity through functional separation.
2Reliability
If complex two-stage combustor geometry is implemented to separate pilot and main combustion, then flame extinction is prevented, but proper temperature profile achievement becomes difficult
Solution Approach 1:
The combustor employs different dome wall configurations for the pilot and main stages. The first dome wall has a specific geometry with fuel injection bores optimized for pilot combustion, while the second dome wall has a different geometry with bores optimized for main stage combustion. This local differentiation allows each stage to achieve its optimal temperature profile independently, ensuring reliable operation and preventing flame extinction while maintaining proper temperature distribution.
3Adaptability or versatility
If increased-complexity geometry is used in two-stage combustors to define separate combustion stages, then pilot and main combustion can be separated, but dynamic range management becomes more difficult
Solution Approach 1:
The combustor design incorporates adjustable fuel injection systems that can dynamically control the fuel flow to each combustion stage. The first fuel injection system and second fuel injection system can be independently regulated to match the desired power setting, allowing dynamic range management despite the physical complexity of the two-stage geometry. This dynamic control capability enables easy operation across different power conditions.
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 enhances temperature control and durability by enabling effective fuel distribution and mixing, improving the operational efficiency and reliability of the gas turbine engine across various power settings.
Implementation Method 1
a first dome wall having a circumferential array of first fuel injection bores radially extending through the first dome wall; a second dome wall having a circumferential array of second fuel injection bores radially extending through the second dome wall
Implementation Method 2
a lobed mixer wall for efficient fuel mixing
Implementation Method 3
a combustion chamber of the combustor; a first combustion stage defined at least by the inner liner wall forward end, the first dome wall and the intermediate wall, a second combustion stage defined at least by the outer liner wall forward end, the second dome wall and the intermediate wall
Data Source
AI summary
A combustor for a gas turbine engine comprises an inner annular liner wall and an outer annular liner wall cooperating to form a combustion chamber of the combustor. A first dome wall has a circumferential array of first fuel injection bores. A second dome has a circumferential array of second fuel injection bores. An intermediate wall extends between the first dome wall and the second dome wall. A first combustion stage is defined by the inner liner wall forward end, the first dome wall and the intermediate wall. A second combustion stage is defined at least by the outer liner wall forward end, the second dome wall and the intermediate wall, the first combustion stage communicating with the first fuel injection bores, the second combustion stage communicating with the second fuel injection bores.