Compressor Bleed Passage for Gas Turbine Engine Thrust
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Solution Overview
Problem
Gas turbine engines face challenges in improving efficiency and thrust output while maintaining or reducing cross-sectional area and volume, and in maintaining operability during transient conditions to avoid stall or surge conditions.
Innovation Solution
The implementation of a gas turbine engine design featuring a turbomachine with a first and second compressor, a third stream bypass passage, and a bleed passage system that extends from the compressor section to the third stream and first bypass passage, allowing for enhanced thrust production without increasing engine size and ensuring stable operation by managing airflow and pressure ratios.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If structures are added to increase thrust output and efficiency, then thrust and efficiency are improved, but cross-sectional area increases
Solution Approach 1:
The bleed passage is nested within the existing compressor structure, utilizing the space between compressor stages and the compressor casing. The passage extends from downstream of the first compressor upstream of the second compressor, effectively using available volume without increasing external dimensions. This nesting approach allows thrust enhancement through improved airflow management while maintaining compact engine geometry.
Solution Approach 2:
The invention utilizes the radial and axial dimensions within the existing compressor cross-section by positioning the bleed passage between compressor stages and routing it through the compressor casing. This three-dimensional utilization of internal space enables airflow redistribution for improved thrust without expanding the engine's external cross-sectional area.
2Use of energy by moving object
If compressor stages are operated at high pressure ratios, then efficiency is improved, but stall or surge conditions may occur during transient operations
Solution Approach 1:
The bleed passage provides a pre-configured airflow redistribution path that activates automatically during transient conditions. By designing the passage structure in advance with appropriate routing between compressor stages, the system prepares a controlled bleed path that prevents stall and surge before these conditions fully develop, maintaining stable operation during rapid transitions.
Solution Approach 2:
The bleed passage acts as an intermediary mechanism between compressor stages, providing a controlled path for airflow redistribution. This intermediate structure mediates the airflow between stages, preventing direct interaction that could cause stall or surge while maintaining the high pressure ratios needed for efficiency during steady-state operation.
Data Source
AI summary
A gas turbine engine includes a turbomachine defining a core flowpath extending through a first compressor and a second compressor, wherein a first compressor frame defines a compressor bypass passage extending from the core flowpath at the first compressor frame; and a forward compressor frame positioned between the first compressor and the second compressor, wherein the forward compressor frame defines at least in part a second portion of the core flowpath at a location downstream of the first portion of the core flowpath, wherein the forward compressor frame defines a compressor bleed passage extending from the core flowpath at a location downstream of the first compressor and upstream of the second compressor to egress a flow of air away from the core flowpath.