Turbine Bucket Flow Control for Gas Turbine Efficiency
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Solution Overview
Problem
Known turbine engines suffer from reduced operating efficiency due to flow energy loss as combustion gases impact stationary stator vanes, which reduces the energy available to rotate the rotor assembly and produce useful work.
Innovation Solution
A combustor system with a first combustor assembly oriented adjacent to the turbine inlet and a second combustor assembly positioned between adjacent turbine bucket assemblies along the combustion gas path, generating a second flow of combustion gases within the path to enhance energy transfer and reduce secondary flow losses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If combustion gases impact stationary stator vanes to channel flow towards turbine buckets, then the combustion gas flow is directed towards adjacent turbine buckets, but flow energy is lost reducing the energy available to rotate the rotor assembly
Solution Approach 1:
The patent extracts the flow direction control function from the stationary stator vanes and relocates it to the rotating turbine buckets themselves. The turbine buckets are designed with specific geometric features that guide combustion gases directly onto the rotor blades, eliminating the need for separate stator vanes and the associated flow energy losses.
Solution Approach 2:
The turbine buckets serve multiple functions simultaneously: they guide combustion gases onto the rotor blades, convert thermal energy to mechanical work, and eliminate the need for separate stator vane assemblies. This multi-functionality consolidates the flow control and energy extraction functions into a single component system.
2Ease of operation
If stationary stator vanes are used to channel combustion gases, then flow direction is controlled, but the structure increases device complexity
Solution Approach 1:
The patent removes the stationary stator vane assemblies entirely from the turbine engine structure. By extracting this component, the design eliminates the complexity of having separate flow control elements while maintaining the ability to direct combustion gases onto the rotor blades through the turbine bucket geometry itself.
Solution Approach 2:
The patent merges the flow direction control function with the turbine bucket structure. The turbine buckets are designed with integrated geometric features that guide combustion gases directly onto the rotor blades, combining what were previously separate functions (stator vanes for flow control, turbine buckets for energy extraction) into a unified component system.
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 described combustor system increases the operating efficiency of the turbine engine by optimizing the flow of combustion gases, reducing energy losses, and extending the useful life of the engine.
Implementation Method 1
The mixture is ignited generating hot combustion gases that are channeled to the turbine inlet
Implementation Method 2
The turbine extracts energy from the combustion gases for powering the compressor, as well as producing useful work to power a load
Implementation Method 3
As the combustion gases impact the stator vanes, at least a portion of the combustion gas flow energy is imparted on the stator vanes. This flow energy loss reduces the combustion gas flow energy available to rotate the rotor assembly
Data Source
AI summary
A combustor system for use in a turbine engine is provided. The turbine engine includes turbine assembly that includes a fluid inlet, a fluid outlet, and a combustion gas path defined therebetween. The combustor system includes a first combustor assembly and a second combustor assembly. The first combustor assembly is coupled to the turbine assembly for channeling a first flow of combustion gases through the turbine assembly. The first combustor assembly is oriented adjacent to the turbine assembly inlet to channel the first flow of combustion gases to the turbine assembly through the turbine assembly inlet. The second combustor assembly is coupled to the turbine assembly along the combustion gas path for channeling a second flow of combustion gases through the turbine assembly.