Monolithic Annular Diffuser for Gas Turbine Compressor Bleed Slots
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Solution Overview
Problem
Existing gas turbine engine bleed slot assemblies suffer from leakage and pressure loss due to joint movements and undesirable airflow paths, leading to inefficiencies in air extraction for cooling and pressurization purposes.
Innovation Solution
A monolithic annular diffuser with smooth air passageways is integrated between stator platforms, eliminating joint leaks and optimizing airflow paths to enhance pressure recovery in the bleed cavity, reducing dead zones and improving structural rigidity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If separate case assemblies are used to create bleed slot openings, then the bleed slots can be formed in the compressor casing, but joint movements create leak paths and pressure loss in the bleed cavity
Solution Approach 1:
The patent merges multiple separate case assemblies into a single monolithic annular ring structure. This integration eliminates the joints between separate cases that caused leak paths and pressure loss, while maintaining the ability to form bleed slot openings in the compressor casing.
2Ease of manufacture
If segmented annular ring assemblies are used, then bleed slot openings can be created, but the separate pieces move relative to each other creating additional leak paths
Solution Approach 1:
The patent combines multiple segmented pieces into a single monolithic annular ring, eliminating relative movement between separate pieces. This integration provides structural rigidity and stability while maintaining the functionality of creating bleed slot openings.
3Productivity
If certain bleed slot shapes are used, then air extraction is enabled, but dead zones form along the slot lengths causing additional pressure losses
Solution Approach 1:
The patent optimizes the local geometry of the air passageways within the monolithic annular ring to eliminate dead zones. By carefully designing the shape and distribution of air passageways, the patent ensures uniform airflow throughout the entire length of the bleed slots, preventing areas of significantly reduced flow velocity that would cause pressure losses.
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 solution increases the pressure recovered in the bleed cavity, enabling more efficient air extraction and utilization for turbine cooling, pressurization, and other applications, while minimizing structural complexity and maintenance requirements.
Implementation Method 1
at least one diffuser is disposed between the first vane platform and the second vane platform. The diffuser includes an entrance opening, an exit opening, and an air passageway between the entrance opening and the exit opening
Data Source
AI summary
A compressor for a gas turbine engine includes a stator and a rotor. The stator includes first and second stator vanes attached to first and second vane platforms, respectively. The rotor includes a plurality of rotor blades that rotate with respect to the stator. An inner stator casing supports the first and second vane platforms and encloses the stator and the rotor. An outer stator casing encloses the inner stator casing, and a bleed cavity is disposed therebetween. At least one diffuser is disposed between the first vane platform and the second vane platform, and is configured to allow air communication between the inner stator casing and the bleed cavity. An exit opening of the diffuser is disposed within the bleed cavity at a location separate from the inner stator casing and the outer stator casing.