Dual Source Cooling Air Shroud for Gas Turbine
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Solution Overview
Problem
Gas turbine engines face challenges in achieving efficient cooling of components, particularly high-pressure turbines, where increased cooling reduces efficiency and requires a trade-off between turbine entry temperature, component life, and specific fuel consumption.
Innovation Solution
A shroud arrangement with a seal segment utilizing two independent cooling circuits, one for the upstream and one for the downstream portion, allowing for dual-source cooling with air supplied at different pressures and temperatures, which are segregated by a bulkhead to maintain thermal and pressure differentials, thereby optimizing cooling efficiency and reducing fuel costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of stationary object
If increased cooling is applied to turbine components, then component life is extended, but efficiency is reduced
Solution Approach 1:
The seal segment is divided into multiple zones with different cooling requirements. The first cooling circuit cools the leading edge region while the second cooling circuit cools the trailing edge region, allowing each area to receive cooling air at appropriate temperatures and pressures tailored to its specific thermal environment, thereby extending component life without excessive energy loss
Solution Approach 2:
The system utilizes two distinct cooling air sources with different temperature and pressure parameters. The first cooling air source provides cooler, lower pressure air for the leading edge, while the second cooling air source provides warmer, higher pressure air for the trailing edge, optimizing the balance between component protection and energy efficiency
2Productivity
If turbine entry temperature is increased, then specific output is improved, but component life is reduced
Solution Approach 1:
Different portions of the seal segment are provided with differentiated cooling strategies. The leading edge receives cooling from the first circuit with air at lower temperature and pressure, while the trailing edge receives cooling from the second circuit with air at higher temperature and pressure, enabling the system to withstand higher turbine entry temperatures while preserving component life
Solution Approach 2:
The seal segment is functionally segmented into multiple cooling zones served by independent cooling circuits. This segmentation allows the system to maintain structural integrity at high temperatures by providing targeted cooling where needed, thus supporting higher turbine entry temperatures for improved specific output
3Productivity
If dual-source cooling is implemented, then cooling efficiency is optimized, but device complexity is increased
Solution Approach 1:
The seal segment is divided into multiple cooling zones with independent cooling circuits. The first cooling circuit serves the leading edge region while the second cooling circuit serves the trailing edge region, allowing optimized cooling efficiency through targeted temperature and pressure control without requiring a completely new complex system
Solution Approach 2:
The dual cooling circuit system uses standard cooling air sources that are already present in the gas turbine engine, making the second cooling air source multi-functional by serving both the seal segment and potentially other components. This approach optimizes cooling efficiency while minimizing additional complexity by utilizing existing engine resources
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 dual-source cooling system effectively manages thermal conditions, reduces fuel consumption, and extends component life by providing targeted cooling to specific areas of the seal segment, improving the overall efficiency and performance of the gas turbine engine.
Implementation Method 1
a first cooling circuit for cooling a first portion of the plate
Implementation Method 2
a second cooling circuit for cooling a second portion of the plate
Implementation Method 3
the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path
Data Source
AI summary
A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described.