Gas Turbine Compressor Support Member Design
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Solution Overview
Problem
In gas turbine engines, relative movement between compressor portions due to fan section movement decreases compression efficiency and complicates access to plumbing connections, particularly when the inlet case supports the compressor.
Innovation Solution
A gas turbine engine design featuring a gear arrangement to drive the fan section, with a compressor section comprising both a first and second compressor, and a turbine section that drives the compressor section and gear arrangement, along with a support member to restrict compressor case movement relative to the inlet case, allowing for simplified maintenance and improved compression efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the inlet case supports the front portion of the compressor, then the compressor is supported during operation, but relative movement between compressor portions occurs due to fan section movement, decreasing compression efficiency
Solution Approach 1:
A separate support member is introduced as an intermediary element between the inlet case and the compressor. This support member specifically restrains relative movement between the front and rear portions of the compressor, preventing rotor tip clearance variation while maintaining the inlet case's support function. The support member acts as a mediator that isolates the compressor from unwanted movements caused by fan section displacement.
2Strength
If the inlet case supports the compressor, then structural support is provided, but access to plumbing connections near the inlet case becomes complicated
Solution Approach 1:
The support function is segmented from the inlet case structure. Instead of the inlet case directly supporting the compressor, a separate support member provides this function. This segmentation allows the inlet case to be designed and positioned for optimal plumbing connection access, while the support member handles the structural support requirement independently.
3Adaptability or versatility
If a gear reduction is incorporated to drive the fan, then the low pressure turbine can drive both the low pressure compressor and the fan at different speeds, but device complexity increases
Solution Approach 1:
The low pressure turbine is designed with multi-functionality, capable of driving both the low pressure compressor and the fan through the gear reduction arrangement. This universal design allows a single turbine to perform multiple functions that would traditionally require separate driving mechanisms, thereby managing complexity while achieving independent speed control.
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 section and a second compressor section. 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 section and a pressure ratio across the second compressor section, and greater than 40. The pressure ratio across the second compressor section is between 7 and 15, and the pressure ratio across the first compressor section is between 4 and 8.