Gas Turbine Bleeding Structure with Partitioning Member
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Solution Overview
Problem
In gas turbine engines, uneven flow of compressed air in the circumferential direction during bleeding leads to unstable combustion and increased engine size due to the need for multiple bleeding ducts and a large manifold.
Innovation Solution
A bleeding structure with an annular partitioning member that separates the bleeding space from the chamber, featuring communication holes and elastic design elements, guides compressed gas uniformly and prevents leakage, allowing for stable combustion without enlarging the engine.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a large number of bleeding ducts are arranged at the outer circumferential portion of the casing, then uniform combustion is achieved, but the engine size becomes large
Solution Approach 1:
The invention divides the single large manifold into multiple smaller manifolds distributed around the combustor. Each manifold serves a specific angular range, allowing blooded air to be distributed more uniformly across the combustor perimeter. This segmentation eliminates the need for a large centralized manifold, reducing overall engine size while maintaining combustion stability.
Solution Approach 2:
The invention transitions from a single-point bleeding location to distributed bleeding locations around the combustor perimeter. By arranging multiple small manifolds at different angular positions rather than one large manifold, the system achieves uniform air distribution without requiring large radial or axial dimensions, thus reducing engine size.
2Reliability
If compressed air is bled to the outside, then combustion temperature is maintained and stability is ensured, but uneven flow in the circumferential direction occurs
Solution Approach 1:
The invention creates different flow paths and pressure distributions at different angular positions around the combustor. Each local manifold is positioned to serve a specific region, ensuring that blooded air is extracted uniformly from different parts of the compressor discharge. This local optimization of bleeding locations and manifold positions achieves circumferential flow uniformity while maintaining overall combustion stability.
Solution Approach 2:
The invention introduces multiple small manifolds as intermediary components between the compressed air flow and the external environment. These manifolds act as distribution nodes that evenly partition and redirect blooded air to different angular positions, preventing uneven flow patterns and ensuring uniform combustion across the combustor perimeter.
3Ease of operation
If a manifold is provided at the outer circumferential portion to collect bled air, then bleeding function is achieved, but the engine size increases
Solution Approach 1:
The invention replaces one large manifold with multiple smaller manifolds distributed around the combustor. Each small manifold handles a portion of the total bleeding flow, allowing the blooded air to be collected and distributed more compactly. This segmentation reduces the volume required for manifold structure while maintaining the complete bleeding function.
Solution Approach 2:
The invention integrates the manifolds within the existing engine structure, nesting them within the available space around the combustor rather than adding external components. The manifolds are positioned to utilize the existing casing volume, eliminating the need for additional external space and preventing engine size increase.
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 ensures stable combustion by uniformly distributing compressed gas and reduces the engine's size by minimizing the number of bleeding ducts required, maintaining even flow and preventing gas leakage.
Implementation Method 1
the compressed gas in the chamber collides with the partitioning member and flows in the circumferential direction, and is subsequently bled through the plurality of communication holes of the partitioning member toward the downstream side
Implementation Method 2
the partitioning member may include a body portion extending in a radial direction, and an outer-diameter-side leg portion and an inner-diameter-side leg portion respectively extending in an axial direction from radially opposite ends of the body portion
Data Source
AI summary
Provided is a structure for bleeding gas from a chamber for receiving compressed gas from a compressor of a gas turbine engine and supplying the compressed gas to a combustor. The structure includes: a turbine casing covering an outer circumference of a turbine; an engine housing forming, between the engine housing and the turbine casing, a bleeding space that communicates with the chamber; a bleeding duct through which compressed gas in the bleeding space is guided to the outside of the engine housing; and an annular partitioning member arranged on an upstream side, relative to the bleeding duct in the bleeding space so as to separate the bleeding space from the chamber, and having a plurality of communication holes through which an upstream side and a downstream side relative to the partitioning member communicate with each other.