Radially Partitioned Gas Turbine Combustor Nozzle
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Solution Overview
Problem
Conventional gas turbine combustors face issues with complex fuel paths and non-uniform fuel distribution to nozzles, making assembly and maintenance difficult and affecting combustion efficiency.
Innovation Solution
A gas turbine combustor design with radially partitioned nozzle units, featuring independent fuel and air plenums and a swirler system for uniform fuel distribution, allowing for easy assembly and disassembly, and improved fuel and air mixing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If fuel is supplied to nozzles through a centralized axial path, then the structure is simple, but fuel distribution to nozzles becomes non-uniform
Solution Approach 1:
The fuel supply system is segmented into multiple independent fuel supply lines, each serving specific nozzles. The fuel supply path is divided into first fuel supply lines extending from the axial center and second fuel supply lines extending from the outer periphery, allowing independent control and uniform distribution of fuel to different nozzle groups.
2Manufacturing precision
If nozzles are arranged radially with complex fuel paths, then fuel distribution can be uniform, but assembly and maintenance become difficult
Solution Approach 1:
The nozzle assembly is segmented into multiple nozzle groups arranged radially, with each group served by dedicated fuel supply lines. This modular segmentation allows each nozzle group to be assembled and maintained independently, simplifying operations while maintaining uniform fuel distribution through the radial arrangement.
Solution Approach 2:
The fuel supply system transitions from a purely axial (one-dimensional) supply path to a two-dimensional radial distribution system. Second fuel supply lines extend from the outer periphery in the radial direction, creating a planar fuel distribution network that improves accessibility for maintenance while achieving uniform fuel delivery to radially arranged nozzles.
3Ease of operation
If fuel supply path is simplified, then assembly is easier, but fuel distribution uniformity deteriorates
Solution Approach 1:
The fuel supply system uses multiple segmented fuel supply lines (first and second fuel supply lines) that can be independently installed and adjusted. This segmentation allows for straightforward assembly of each line while collectively achieving uniform fuel distribution across all nozzles through their coordinated radial and axial arrangement.
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 ensures uniform fuel distribution to each nozzle, simplifies maintenance, and enhances combustion efficiency by facilitating smooth mixing of fuel and air, leading to improved performance and reduced NOx levels.
Implementation Method 1
a swirler that rotates a mixed gas of the fuel and the air
Implementation Method 2
a fuel injection port that communicates with the swirler plenum to inject fuel residing in the swirler plenum into a space between the outer tube and the inner tube
Data Source
AI summary
A gas turbine combustor includes a combustion chamber coupled to a nozzle unit that is radially partitioned into plural regions. Each region includes a nozzle casing; a nozzle supplied with fuel and air to produce a mixed gas of the fuel and the air and configured to be inserted into the nozzle casing and to inject the mixed gas into the combustion chamber; a fuel supply section coupled to an outer peripheral surface of the nozzle casing to supply the fuel to the nozzle through the outer peripheral surface; a fuel plenum formed in the nozzle casing to receive the fuel from the fuel supply section; and an air plenum formed in the nozzle casing toward the combustion chamber to receive a portion of the air supplied to the nozzle unit, the portion of air introduced to the air plenum through a first opening formed in the nozzle casing.