Gas Turbine Stator Vane Positioning for Cooling Reduction
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Solution Overview
Problem
In gas turbines, the flow of high-temperature working fluid into gaps between the combustor tail pipe and first-stage turbine stator vanes leads to energy loss and heating, requiring excessive cooling, which disturbs the fluid flow and complicates cooling of the turbine blades.
Innovation Solution
The first-stage turbine stator vanes are positioned downstream of the sidewalls, with leading edges placed in relatively cool flows behind the sidewalls, reducing direct exposure to high-temperature gas and minimizing flow disturbances, thus reducing the need for cooling fluid and enhancing cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If the first-stage turbine stator vanes are brought close to the combustor, then integration is improved and cooling fluid requirement is reduced, but flow disturbance occurs at the connecting portion between the inner wall and the stator vanes
Solution Approach 1:
The patent applies dimensionality change by transitioning from a conventional configuration where stator vanes are aligned with combustor exit to a positioned configuration where stator vanes are located downstream of the combustor exit. This spatial repositioning in the flow direction (dimensional change) allows the stator vanes to be exposed to cooler, less turbulent flow while maintaining close proximity to the combustor, thus reducing cooling fluid requirements without causing flow disturbance.
2Quantity of substance
If the leading edges of the first-stage turbine stator vanes are surrounded by the rear end of the combustor, then cooling fluid is not required, but flow disturbance occurs at the connecting portion
Solution Approach 1:
The patent applies local quality by creating a specific flow condition at the local region where the stator vanes are positioned downstream of the combustor exit. In this localized area, the flow is naturally cooler and less turbulent, allowing the stator vanes to operate without additional cooling while maintaining efficient flow characteristics. This local optimization does not require changes to the overall combustor or turbine design.
3Device complexity
If the first-stage turbine stator vanes are positioned close to the combustor, then integration is improved, but it becomes difficult to supply cooling fluid and form a film-like layer
Solution Approach 1:
The patent applies preliminary action by utilizing the pre-existing flow conditions downstream of the combustor exit. The flow in this region is naturally cooler and less turbulent before it reaches the stator vanes, so no additional cooling fluid supply mechanism is needed. The stator vanes are positioned to take advantage of this pre-conditioned flow, eliminating the need for complex cooling fluid delivery systems while maintaining close integration with the combustor.
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 configuration suppresses energy losses, reduces cooling fluid requirements, and improves the overall efficiency of the gas turbine by minimizing the disturbance to the combustion gas flow and heat transfer to the turbine blades.
Implementation Method 1
the leading edges of the first-stage turbine stator vanes disposed downstream of the sidewalls to end portions of the sidewalls closer to the turbine portion is equal to or less than a spacing between an internal surface of the sidewall of the one pipe piece and an internal surface of the sidewall of the other pipe piece
Implementation Method 2
the leading edges of the first-stage turbine stator vanes are heated by the high-temperature working fluid that has flowed into the gaps
Data Source
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AI summary
Provided is a structure for connecting a combustor (3), which generates a combustion gas inside cylinders (33), to a turbine unit (4), which generates a rotational motive force by sequentially passing the combustion gas through turbine stages comprising turbine stator vanes (44SV) and turbine rotor blades. At least part of the one-stage turbine stator vane (44SV) closest to the combustor (3) is disposed downstream of side walls (34) in one cylinder (33) and another cylinder (33) adjacent thereto. The distance from the leading edge of the one-stage turbine stator vane (4SV) disposed downstream of the side wall (34) in the cylinder (33) to the turbine unit (4) end of the side wall (34) is less than or equal to the spacing between the inner surface of the side wall (34) of the one cylinder (33) to the inner surface of the side wall (34) of the other cylinder (33).