Compressor Spacer Radial Orifices Cooling
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Solution Overview
Problem
High temperatures in the compressor section of gas turbine engines reduce the lifetime of components, limiting operating pressures and efficiency, despite cooling arrangements, which often fail to effectively manage temperature gradients across compressor stages.
Innovation Solution
A spacer system for the high-pressure compressor stage with radially arranged orifices and a heat exchanger to condition cooling air, allowing for optimal temperature control by directing cooling air in opposite flow directions through the compressor stages, supplemented by additional cooling air to maintain efficiency and prevent leakage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If higher operating pressures are used to improve compressor efficiency, then engine efficiency is improved, but component lifetime is reduced due to high temperatures
Solution Approach 1:
The spacer introduces localized cooling by directing cooling air through radially arranged orifices to specific high-temperature zones between compressor stages. This creates non-uniform temperature distribution where cooling is applied precisely where needed (at the spacer location) while other areas maintain their thermal characteristics, allowing the system to operate at higher pressures without uniform temperature reduction throughout the entire compressor section.
2Duration of action of stationary object
If cooling air is introduced to reduce temperatures, then component lifetime is improved, but temperature gradients across compressor stages are not effectively managed
Solution Approach 1:
The spacer divides the cooling function into multiple segments by incorporating radially arranged orifices that distribute cooling air across different radial positions between compressor stages. This segmented approach to cooling allows temperature management at multiple discrete locations rather than a single centralized cooling point, better addressing the temperature gradient problem across the compressor stage interface.
Solution Approach 2:
The spacer introduces a radial dimension to cooling air distribution by arranging orifices radially and directing cooling air in opposite flow directions. This radial arrangement adds a dimensional aspect to cooling that complements the axial flow direction, creating a more comprehensive three-dimensional cooling pattern that effectively manages temperature gradients in both axial and radial directions between compressor stages.
3Temperature
If cooling air is directed through compressor stages, then temperature control is optimized, but cooling air may mix with core airflow reducing compressor efficiency
Solution Approach 1:
The spacer extracts cooling air from the main core airflow path by introducing it through radially arranged orifices in the spacer structure itself. This extraction occurs at the spacer location between compressor stages, separating the cooling air introduction function from the main axial core airflow path. The cooling air is taken out and distributed radially, preventing it from mixing with and disrupting the core airflow that drives compressor efficiency.
Solution Approach 2:
The spacer acts as an intermediary structure that mediates between the cooling air supply and the compressor stages. It receives cooling air and distributes it through radially arranged orifices to the compressor stage interface, serving as a intermediate device that controls the interaction between cooling air and core airflow. This intermediary function allows temperature control to be achieved while maintaining the separation and independence of the core airflow path.
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 spacer system effectively reduces temperature gradients across compressor stages, enhancing component lifetimes and overall engine efficiency by optimizing cooling air distribution and flow, while maintaining compressor efficiency by preventing mixing with core airflow.
Implementation Method 1
a heat exchanger to condition cooling air
Implementation Method 2
The spacer system effectively reduces temperature gradients across compressor stages, enhancing component lifetimes and overall engine efficiency by optimizing cooling air distribution and flow
Data Source
Figure 1
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AI summary
An example method of cooling a compressor section of a gas turbine engine includes diverting a flow from a compressor through a heat exchanger, the flow moving from the compressor in a first direction, and moving the flow from the heat exchanger back to the compressor in a second direction. An example spacer for a compressor of a gas turbine engine includes a first side portion, a second side portion spaced apart from the first side portion, and a middle web arranged between the first and second side portions. At least one of the first and second side portions and the middle web include at least one orifice to communicate flow in a direction that is different from a core flowpath flow direction. An example compressor including the spacer is also disclosed.