Gas Turbine Inlet Guide Vane Shroud and Baffle Assembly
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Solution Overview
Problem
Gas turbine engines experience diminished performance due to excessive vibration and turbulence in air-filled cavities between the rotor and stator, particularly between a row of inlet guide vanes (IGVs) and the first stage of the high pressure compressor (HPC) rotor, which is exacerbated by the lack of effective shrouding and baffling.
Innovation Solution
A shroud and baffle assembly that includes a shroud with a seal assembly to form a seal with rotating teeth on the rotor and a baffle extending circumferentially about the engine axis, effectively filling and separating air in the cavities to reduce vibration and turbulence while maintaining conformance to strict shroud forward shape requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a shroud is used to fill air-filled cavities between rotor and stator, then vibration and turbulence are reduced, but the shroud forward shape requirements become difficult to meet
Solution Approach 1:
The shroud is divided into multiple segments (first shroud segment, second shroud segment, third shroud segment) that can be independently positioned and configured. This segmentation allows each segment to be optimized for its specific function - some segments fill the cavity to reduce vibration while others maintain the required forward shape, resolving the contradiction between vibration reduction and shape requirements.
Solution Approach 2:
Different portions of the shroud structure are given different properties and configurations. The shroud segments have varying radial positions, axial lengths, and geometries tailored to local requirements - some areas prioritize cavity filling for vibration control while other areas prioritize shape conformity, allowing simultaneous optimization of both contradictory requirements.
2Shape
If the air-filled cavity is not shrouded and baffled, then the shroud forward shape requirements can be met, but excessive vibration and turbulence occur leading to diminished engine performance
Solution Approach 1:
The shroud is segmented into multiple independently configurable sections that can simultaneously maintain the required forward shape while filling air-filled cavities. The segmented structure allows specific segments to extend into cavities for vibration control without compromising the overall forward shape appearance, thus improving engine performance while meeting shape requirements.
Solution Approach 2:
The shroud segments act as intermediary structures between the rotor and stator, filling air-filled cavities that cause vibration and turbulence. By introducing these intermediate shroud segments, the harmful cavity effects are eliminated while the shroud maintains its required forward shape, thereby improving engine performance without sacrificing shape compliance.
3Ease of manufacture
If a single-piece shroud is used, then manufacturing is simpler, but the ability to effectively fill cavities and reduce vibration is limited
Solution Approach 1:
The shroud is divided into multiple segments that can be manufactured separately and then assembled. This segmentation enables each segment to be precisely configured to fill specific air-filled cavities and target vibration sources, providing superior vibration control compared to a single-piece design. The segmented approach maintains reasonable manufacturing complexity while dramatically improving vibration reduction capability.
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 shroud and baffle assembly enhances gas turbine engine performance by reducing air-filled cavity effects on flow paths, thereby improving engine efficiency and maintaining compliance with shape requirements.
Implementation Method 1
a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of the gas turbine engine
Data Source
AI summary
A system for an inlet guide vane shroud and baffle assembly includes a shroud. The shroud includes a first end configured to couple to an annular support member of the gas turbine engine, and a second end. The shroud also includes a distal end including an axially aft extending lip, and a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of the gas turbine engine. The shroud further includes an arcuate shroud body extending between the distal end and the second end. The shroud and baffle assembly also includes a baffle coupled to an aft side of the shroud. The baffle includes a radially outward end coupled to the aft side, a radially inward end coupled to the axially aft extending lip, and an arcuate baffle body extending there between. Both the shroud and the baffle extend circumferentially about a central axis.