Turbine Mixing Chamber for Compressor Exit Temperature Control
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Solution Overview
Problem
Turbine engine components, particularly the high pressure compressor, face elevated temperatures due to increased pressure at the exit of the high pressure compressor, necessitating effective cooling methods to prevent damage, but existing cooling designs often use air that is too cool and inefficiently conditioned.
Innovation Solution
A mixing chamber is introduced between the compressor and combustor sections, utilizing a diffuser case strut with a cooled air inlet tube and ambient air mixing to achieve a desired temperature for effective cooling, with seals and metering holes ensuring proper airflow and temperature conditioning.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cool air from bypass flowpath is directed onto high pressure compressor components, then cooling effect is enhanced, but the air temperature becomes too low causing inefficient cooling
Solution Approach 1:
A mixing chamber is introduced as an intermediary device between the bypass air source and the high pressure compressor components. The mixing chamber combines cool bypass air with warmer compressor discharge air in controlled proportions, producing air at an optimal intermediate temperature that efficiently cools the components without being excessively cold
Solution Approach 2:
The invention changes the temperature parameter of the cooling air by mixing two air streams of different temperatures. The mixing chamber allows continuous adjustment of the cooling air temperature by controlling the mixing ratio, transforming the cooling air from too-cold bypass air to optimally-conditioned air for effective component cooling
2Productivity
If pressure at exit of high pressure compressor is increased to improve efficiency, then bypass ratio efficiency increases, but temperature at compressor exit (T3) becomes excessively elevated
Solution Approach 1:
The mixing chamber serves as an intermediary cooling system that allows the high pressure compressor to operate at high exit pressures and temperatures for improved efficiency, while separately conditioning the cooling air to the appropriate temperature for component protection
Solution Approach 2:
The invention segments the air flow into separate functional streams: one stream handles the high-pressure main flow for efficiency, while another stream is diverted through the mixing chamber to provide controlled cooling. This segmentation allows independent optimization of both efficiency and cooling requirements
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 mixing chamber effectively conditions air to a suitable temperature for cooling turbine engine components, enhancing cooling efficiency and addressing the issue of elevated T3 temperatures by mixing overcooled air with ambient air, thereby improving the cooling of critical components like rotor blades and compressor hubs.
Implementation Method 1
mixing chamber is introduced between the compressor and combustor sections, utilizing a diffuser case strut with a cooled air inlet tube and ambient air mixing to achieve a desired temperature for effective cooling
Implementation Method 2
the mixing chamber wall isolates the mixing chamber from a diffuser chamber, and the mixing chamber wall includes a seal having local penetrations such that diffuser air can travel from the diffuser into the mixing chamber
Data Source
AI summary
A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section.