Turbine Cooling Flow Control Assembly
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Solution Overview
Problem
Gas turbine engines face efficiency losses due to the extraction of air for cooling, which increases fuel consumption and costs, as conventional methods like heat exchangers and blade cooling techniques add weight, complexity, and maintenance costs.
Innovation Solution
A flow control assembly is introduced, comprising a first and second flow control device with an orifice and meter device, coupled to the compressor and turbine, allowing for the extraction and control of cooling flow, specifically directing cooler air from the mid-span of the compressor exit guide vane to the turbine blade, reducing the need for heat exchangers and minimizing air extraction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If heat exchangers are used to reduce cooling air temperature, then cooling efficiency is improved, but weight and cost increase
Solution Approach 1:
The invention extracts cooler air from the mid-span region of the compressor exit guide vane, separating the cooling function from the main hot gas path. This eliminates the need for heat exchangers by directly utilizing cooler compressed air from a specific location in the compressor, thereby reducing weight while maintaining cooling effectiveness.
Solution Approach 2:
The invention introduces flow control devices as intermediaries to regulate and direct the cooling air flow from the compressor to the turbine blade. These devices control the extraction and distribution of cooling air, enabling temperature management without requiring additional heat exchange equipment.
2Temperature
If heat exchangers are used to reduce cooling air temperature, then cooling efficiency is improved, but device complexity increases
Solution Approach 1:
The invention simplifies the cooling system by extracting cooler air directly from the compressor's mid-span region and directing it to the turbine blade through flow control devices. This eliminates complex heat exchanger assemblies and reduces overall system complexity while maintaining effective cooling.
Solution Approach 2:
The compressor's own structure is utilized to provide cooling air by extracting it from the mid-span region of the exit guide vane. The system serves itself by using the compressor's operational flow to provide cooling, eliminating the need for separate, complex cooling subsystems.
3Reliability
If more air is extracted from the compressor for cooling, then turbine blade cooling effectiveness is improved, but fuel consumption increases
Solution Approach 1:
The invention applies local quality by extracting air specifically from the mid-span region of the compressor exit guide vane, where the air is naturally cooler. This localized extraction provides effective cooling with minimal air extraction, reducing the impact on compressor performance and fuel consumption while maintaining turbine blade cooling effectiveness.
Solution Approach 2:
The invention changes the parameters of air extraction by targeting a specific location (mid-span of exit guide vane) with specific temperature characteristics. By adjusting the extraction location and using flow control devices to regulate the flow rate, the system achieves effective cooling with optimized air extraction that minimizes fuel consumption penalties.
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 solution enhances gas turbine efficiency, reduces fuel consumption, and lowers operational and maintenance costs by using a controlled, lower-temperature cooling air flow directly from the compressor, eliminating the need for heat exchangers and minimizing air extraction, thereby improving turbine performance.
Implementation Method 1
an orifice device coupled to the compressor vane and a meter device coupled to the orifice device, wherein the orifice device is configured to direct the cooling flow to the meter device
Implementation Method 2
the meter device is configured to meter the cooling flow into at least one of the first flow path and the second flow path
Implementation Method 3
directing cooler air from the mid-span of the compressor exit guide vane to the turbine blade
Data Source
AI summary
A flow control assembly for controlling cooling flow of a turbine engine is provided. The flow control assembly includes a first flow control device having a first sidewall and a second sidewall. The first sidewall is coupled to a compressor vane and is configured to define a first flow path from a compressor to a turbine vane. The second sidewall is coupled to a compressor vane and is configured to define a second flow path from the compressor to a turbine blade. A second flow control device is coupled to the compressor and includes an orifice device coupled to the compressor vane and a meter device coupled to the orifice, wherein the orifice is configured to direct a cooling flow to the meter device. A controller is configured to control the meter device to facilitate regulating the cooling flow into at least one of the first flow path and the second flow path.