Inlet Bleed Heat Control System with Ejector Mixing
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Solution Overview
Problem
Current inlet bleed heat manifolds in gas turbine engines require a minimum bleed heat flow rate for even flow distribution, leading to excess flow that results in output and heat rate losses, as they are often larger than the actual requirements for operating limit line protection and anti-icing protection.
Innovation Solution
An inlet bleed heat control system with an ejector that mixes compressor discharge air and ambient air, allowing for improved flow control at minimum flow levels by creating a mixed flow for use in the inlet bleed heat manifold, and a bypass line to ensure only the necessary flow is used, reducing excess bleed heat.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If a large inlet bleed heat manifold is used to ensure even flow distribution, then flow distribution is improved, but minimum flow rate requirements increase leading to excess bleed heat flow
Solution Approach 1:
The inlet bleed heat manifold is divided into multiple smaller flow distribution sections or zones, each capable of distributing flow independently. This segmentation allows the system to maintain even flow distribution across the manifold while reducing the total minimum flow rate requirement, as each segment requires less flow to function properly compared to a single large manifold.
2Reliability
If minimum bleed heat flow is increased to protect against compressor surge, then compressor protection is improved, but gas turbine output and efficiency are reduced
Solution Approach 1:
The bleed heat flow rate is made dynamically adjustable rather than fixed at a high minimum level. The system incorporates flow control mechanisms that allow the bleed heat flow to be optimized in real-time based on operating conditions, maintaining sufficient flow for compressor protection while minimizing excess flow that would reduce turbine output and efficiency.
3Loss of energy
If bleed heat flow rate is reduced to improve efficiency, then gas turbine efficiency is improved, but flow distribution uniformity deteriorates
Solution Approach 1:
Different sections of the inlet bleed heat manifold are designed with locally optimized characteristics, such as varying passage sizes, shapes, or flow control element configurations. This allows each local region to maintain uniform flow distribution even when the overall system operates at reduced total flow rates, thereby preserving efficiency while ensuring proper flow distribution.
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 solution allows for precise control of the bleed heat flow rate, reducing output and heat rate losses, thereby improving gas turbine efficiency and output by limiting the bleed heat flow to about 0% to 1% of compressor airflow, compared to conventional rates of 0.5% to 1%.
Implementation Method 1
mixing the compressor discharge air and the ambient air in the ejector
Implementation Method 2
an ejector in communication with the inlet bleed heat manifold such that the ejector is in communication with a flow of compressor discharge air and a flow of ambient air for improved flow control
Data Source
AI summary
The present application provides an inlet bleed heat control system for a compressor of a gas turbine engine. The inlet bleed heat control system provides an inlet bleed heat manifold and an ejector in communication with the inlet bleed heat manifold such that the ejector is in communication with a flow of compressor discharge air and a flow of ambient air.