Gas Turbine Compressor Bleed Path Vortex Design
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Solution Overview
Problem
Existing gas turbine engines face inefficiencies due to pressure losses in the bleed path, which hinder effective cooling and sealing of turbine components, leading to reduced engine efficiency and increased fuel consumption.
Innovation Solution
The design incorporates a bleed path with an annular free vortex passage and circumferentially spaced forced vortex passages through the compressor's second disk, optimizing air flow from the compressor to the turbine, reducing the need for the rotor to increase circumferential velocity, thereby minimizing pressure and temperature increases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If a conventional bleed path is used through the compressor, then air can be bled from the compressor to the turbine, but pressure losses occur in the bleed path which reduce engine efficiency
Solution Approach 1:
The bleed path is segmented into multiple passages (first passage, second passage, third passage) that are distributed through different disks of the rotor. This segmentation allows the bleed air to be extracted at multiple stages with lower pressure losses compared to a single long passage, as each segment operates with smaller pressure differentials.
Solution Approach 2:
The bleed path transitions from a conventional axial arrangement to a three-dimensional configuration that extends radially and circumferentially through the rotor disks. The passages are arranged to exploit the radial and circumferential dimensions, creating a more efficient flow path that reduces the length and resistance of the bleed path while maintaining effective cooling and sealing.
2Reliability
If the rotor increases circumferential velocity to maintain cooling and sealing, then turbine cooling and sealing are effective, but the work required by the rotor increases
Solution Approach 1:
The bleed air is extracted at multiple stages before it would naturally reach higher pressure regions, allowing the cooling and sealing functions to be performed with air at lower pressures. This preliminary extraction prevents the need for the rotor to work harder to maintain the required cooling and sealing pressures, as the bleed path provides the necessary pressure distribution in advance.
Solution Approach 2:
The invention changes the pressure and temperature parameters of the bleed air by extracting it at multiple stages through different disks. This creates a more favorable pressure gradient that reduces the work required by the rotor while maintaining the effectiveness of turbine cooling and sealing, as the multi-stage extraction optimizes the thermodynamic parameters of the bleed air.
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 configuration reduces the work required by the rotor, minimizing pressure losses and temperature increases, enhancing engine efficiency and reducing fuel consumption while maintaining effective cooling and sealing.
Implementation Method 1
The entrance of the bleed path may comprise an annular first passage that defines a free vortex passage. The bleed path may further comprise at least one second passage having a first end communicating with the first passage, the second passage extending through the second disk and defining a forced vortex passage.
Data Source
AI summary
A gas turbine engine includes a compressor for generating compressed air. The compressor includes a rotor defined by a plurality of axial disks including a first disk and a second disk. A first row of blades extends radially outwardly from the first disk, and a second row of blades extends radially outwardly from the second disk. A row of cantilevered vanes is located at an axial location between the first row of blades and the second row of blades. A bleed path extends at least partially through the second disk and includes an entrance at an axial location between the first row of blades and at least a portion of the row of cantilevered vanes. The entrance communicates with a compressed air flowpath through the compressor.