Compressor Bleed Air Slot for Gas Turbine Efficiency
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Solution Overview
Problem
Gas turbine engines face inefficiencies due to the increased demand for cooling airflow from the compressor section, which reduces overall engine efficiency and compressor performance, particularly because of restrictions in existing cooling airflow passages.
Innovation Solution
The design incorporates a bleed air slot within the compressor section with a radially increasing inlet and outlet area, optimized for efficient airflow diffusion and reduced aerodynamic losses, allowing for improved communication of cooling airflow to the turbine section, thereby minimizing the need for additional cooling air from the compressor.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If cooling airflow passages are restricted, then turbine section cooling is maintained, but compressor efficiency and overall engine efficiency decrease due to increased cooling air demand
Solution Approach 1:
The patent changes the geometric parameters of the cooling airflow passages, specifically increasing the passage cross-sectional area and optimizing the bleed air slot dimensions (inlet area A1, outlet area A2, and length L). These parameter changes reduce flow restrictions while maintaining cooling effectiveness, thereby resolving the contradiction between reliable turbine cooling and engine efficiency.
2Loss of energy
If cooling airflow passages are expanded to reduce restrictions, then engine efficiency improves, but turbine section cooling effectiveness may be compromised
Solution Approach 1:
The patent applies local quality by creating non-uniform distribution of cooling airflow through strategically positioned bleed air slots with specific area ratios (A2/A1) at different locations in the compressor section. This allows optimized cooling delivery to the turbine section while minimizing overall air extraction from the compressor, thus improving efficiency without compromising cooling reliability.
3Reliability
If more cooling air is drawn from the compressor, then turbine section cooling is enhanced, but compressor efficiency decreases
Solution Approach 1:
The patent implements preliminary action by pre-cooling the compressor discharge air through the optimized cooling passages before it enters the turbine section. This preliminary cooling action reduces the temperature of the air requiring to be extracted from the compressor, thereby reducing the total amount of cooling air needed and preserving compressor efficiency while ensuring adequate turbine cooling.
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 enhances compressor efficiency and overall engine efficiency by reducing the amount of cooling air required, leading to improved power transfer and reduced thermal losses.
Implementation Method 1
Air flow drawn from the compressor increases the efficiency of the compressor section
Implementation Method 2
optimized for efficient airflow diffusion
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
A disclosed gas turbine engine includes a case for a case for a compressor section including a bleed air slot. The bleed air slot includes an inlet having a first area radially inward of an outlet having a second area with the second area being greater than the first area. The bleed air slot further includes a center portion disposed along a radial line extending from an axis of the engine and an elongated portion extending from the opening at an angle relative to a line normal to the radial line.