Squealer Tip Cooling Channel for Turbine Blade Heat Control
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Solution Overview
Problem
Gas turbine engine components, particularly turbine blades, face challenges in managing high thermal loads due to exposure to high-temperature combustion gases, leading to inefficiencies in cooling and aerodynamic performance.
Innovation Solution
The design incorporates an internal squealer tip cooling channel within the blade tip, formed by a first and second squealer tip rail and a cap, which connects to an internal cooling circuit via supply apertures, allowing for internal cooling and reducing the need for external cooling fluid flow, thereby enhancing thermal protection and aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If external cooling fluid flow is used to cool the squealer tip, then thermal protection is achieved, but aerodynamic performance deteriorates and cooling fluid consumption increases
Solution Approach 1:
The cooling channel is nested within the squealer tip structure itself, with the channel cavity formed inside the tip and the cooling fluid flowing through this internal cavity. The squealer tip cap encloses the cooling channel, creating a nested configuration where the cooling system is integrated within the structural component rather than being external.
Solution Approach 2:
The cooling fluid acts as an intermediary substance that absorbs thermal energy from the squealer tip through the internal cooling channel walls. The fluid flows through the channel, absorbing heat from the hot squealer tip material, and carries this thermal energy away from the component.
2Temperature
If cooling fluid is supplied to the squealer tip, then thermal loading is reduced, but the amount of cooling fluid required increases system complexity
Solution Approach 1:
The cooling channel is merged with the squealer tip structural component, forming an integrated assembly. The channel walls are formed as part of the tip structure itself, and the tip cap is joined to the tip rails to enclose the channel, creating a unified component rather than separate cooling and structural elements.
Solution Approach 2:
The squealer tip structure serves multiple functions: it provides the aerodynamic sealing function of a traditional squealer tip while simultaneously housing the internal cooling channel. The tip rails and cap that form the structural enclosure also define the cooling fluid passage, combining structural and thermal management functions in a single component.
3Productivity
If the squealer tip is exposed to high temperature combustion gases, then aerodynamic function is maintained, but thermal damage occurs
Solution Approach 1:
The high temperature combustion gases that would otherwise cause thermal damage are utilized to drive the cooling system. The temperature differential between the hot gases and the cooling fluid creates the heat transfer driving force needed for effective cooling, converting the harmful thermal exposure into the beneficial thermal gradient required for heat removal.
Solution Approach 2:
Cooling fluid is supplied to the internal cooling channel before the squealer tip reaches critical temperatures. The cooling system is pre-configured and ready to absorb thermal energy, preventing thermal damage before it occurs rather than attempting to repair or respond after damage has happened.
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 solution effectively reduces thermal loading on the squealer tip, minimizes the amount of cooling fluid required, and improves the aerodynamic efficiency of the gas turbine engine by maintaining a uniform temperature and reducing aerodynamic losses.
Implementation Method 1
passing of a cooling fluid, such as cooling air, across or through a portion of the component
Implementation Method 2
The blade tip, the first and second squealer tip rails, and the squealer tip cap may define an internal squealer tip cooling channel
Data Source
AI summary
A gas turbine engine component may include an airfoil extending radially from a base to a blade tip, the airfoil including a pressure sidewall and a suction sidewall each extending between a leading edge and a trailing edge opposite the leading edge, an internal cooling circuit extending from the base to the blade tip; and a squealer tip. The squealer tip may include a first and a second squealer tip rail adjacent to the first squealer tip rail, and a squealer tip cap extending between the first and second squealer tip rails. The blade tip, the first and second squealer tip rails, and the squealer tip cap may define an internal squealer tip cooling channel. The blade tip may define a supply aperture that fluidly connect the internal cooling circuit and the internal squealer tip cooling channel.