Gas Turbine Compressor Support Layout for Stable Tip Clearance
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Solution Overview
Problem
Existing gas turbine engine designs face issues with relative movement between compressor portions, which decreases compression efficiency and complicate access to plumbing connections, particularly due to the support of the compressor by the inlet case.
Innovation Solution
A gas turbine engine design incorporating a fan section with a gear arrangement, a compressor section with multiple compressors, and a turbine section that drives the gear arrangement, which includes a support member to restrict movement of the compressor case relative to the inlet case, and positions the plumbing connection area upstream for easier access.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the compressor is supported by the inlet case, then the compressor structure is simplified, but relative movement between compressor portions occurs which decreases compression efficiency
Solution Approach 1:
The compressor support function is segmented from the inlet case to a dedicated support member, allowing the inlet case to focus on air guidance while the support member maintains compressor position stability, resolving the conflict between structural simplicity and compression efficiency
Solution Approach 2:
A dedicated support member acts as an intermediary between the inlet case and the compressor, providing stable support while allowing the inlet case to remain simple and focused on its primary function of guiding air into the compressor
2Device complexity
If the compressor is supported by the inlet case, then the support structure is simplified, but access to plumbing connections near the inlet case becomes complicated
Solution Approach 1:
The support function is extracted from the inlet case and assigned to a dedicated support member, creating clear spatial separation that allows plumbers to access connections near the inlet case without interference from support structures
Solution Approach 2:
The support member is positioned in a different spatial dimension relative to the inlet case, allowing plumbing connections to be accessed from directions not blocked by the support structure, improving maintenance accessibility
3Adaptability or versatility
If relative movement between compressor portions is allowed, then the structure is more flexible, but rotor tip clearances vary which decreases compression efficiency
Solution Approach 1:
The support member is designed with controlled flexibility that allows minimal movement to accommodate thermal expansion and operational variations, while maintaining rotor tip clearances within acceptable tolerances to preserve compression efficiency
Solution Approach 2:
The support member's mechanical properties are optimized to allow specific ranges of movement under certain conditions while preventing excessive movement that would affect rotor tip clearances, balancing structural adaptability with manufacturing precision
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 design reduces relative movement between compressor portions, enhances compression efficiency, and simplifies maintenance by improving access to plumbing connections, leading to reduced maintenance time and cost.
Implementation Method 1
A turbine section is configured to drive the compressor section and the gear arrangement
Implementation Method 2
a gear arrangement configured to drive the fan section
Implementation Method 3
a compressor for compressing air and delivering it downstream into a combustion section
Data Source
AI summary
A gas turbine engine includes, among other things, a propulsor section including a propulsor, a core engine, a gear arrangement that drives the propulsor. A compressor section includes a first compressor and a second compressor. A turbine section includes a first turbine and a second turbine. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor and a pressure ratio across the second compressor, and greater than 40. The pressure ratio across the high pressure compressor is no more than 15, and the pressure ratio across the low pressure compressor is at least 4.