Bleed Valve Assembly Routing Duct Through Core Turbine Frame
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Solution Overview
Problem
Gas turbine engines face challenges in increasing available space within the under-cowl area without enlarging the core turbine engine or core cowl, as accessory systems and components require more room due to advancements in technology.
Innovation Solution
A bleed air assembly is introduced, featuring a bleed valve positioned in the liner and a duct extending to the casing, allowing airflow to be bled from the core air flowpath and redirected radially outward through the bypass passage, thereby optimizing space utilization within the under-cowl area.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If the core turbine engine or core cowl is enlarged to provide additional room in the under-cowl area, then the available space for accessory systems and enabling components is increased, but the size of the core turbine engine increases
Solution Approach 1:
The duct is routed through the core turbine frame assembly in a three-dimensional path that utilizes vertical and radial spaces rather than only axial length. The duct extends from the bleed valve in the liner, through the frame assembly, to the casing, effectively using the depth and height dimensions of the engine to accommodate the duct without increasing the overall engine length.
Solution Approach 2:
The duct is positioned within the core turbine frame assembly, nesting the duct inside the existing structural framework of the engine. This allows the duct to occupy space that is already allocated for the frame assembly, rather than requiring additional external space.
2Adaptability or versatility
If accessory systems and enabling components are added to meet advancing technology requirements, then the functionality and capability of the gas turbine engine are improved, but the available space within the under-cowl area is reduced
Solution Approach 1:
The bleed air system is segmented into distinct components: a bleed valve positioned in the liner, a duct routed through the core turbine frame assembly, and an outlet at the casing. This segmentation allows each component to be optimally positioned in available spaces, with the duct utilizing the frame assembly volume rather than competing for under-cowl space.
Solution Approach 2:
The duct routing transitions from a potential two-dimensional planar layout to a three-dimensional path through the frame assembly, utilizing vertical and radial dimensions to accommodate the duct and create additional under-cowl space for accessory systems.
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 bleed air assembly effectively increases available space within the under-cowl area without enlarging the core turbine engine, enhancing operational efficiency and accommodating additional components by redirecting airflow in a compact and efficient manner.
Implementation Method 1
a bleed valve positioned in the liner and a duct in airflow communication with the bleed valve and defining an outlet
Data Source
AI summary
A gas turbine engine includes a first compressor, a casing surrounding the first compressor, and a liner extending forward from the first compressor. The gas turbine engine also includes a core turbine frame assembly extending between the liner and the casing and a bleed air assembly. The bleed air assembly includes a bleed valve positioned in the liner, and a duct in airflow communication with the bleed valve and defining in outlet. The duct is positioned within the core turbine frame assembly and extends to the casing.