Turbine Blade Cover Plate Flow Inducer for Ambient Air Cooling
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Solution Overview
Problem
Existing gas turbine engines face inefficiencies due to the need to bleed compressor air for cooling the last stage turbine blades, which reduces engine efficiency, and there is a need for an efficient system to introduce sufficient ambient air for cooling these blades.
Innovation Solution
A flow inducer assembly integrated into seal plates of the rotor disk, utilizing centrifugal and paddle-like mechanisms to drive ambient air into the disk cavities and turbine blades for cooling, eliminating the need for compressor bleed air.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If compressor air is bled for cooling turbine blades, then turbine blade cooling is achieved, but engine efficiency deteriorates
Solution Approach 1:
The invention extracts the cooling function from the compressor bleed air system and relocates it to ambient air sourced from the engine inlet. The flow inducer assembly captures ambient air and directs it through the rotor disk cavities to the turbine blades, separating the cooling function from the compressor system and eliminating the energy loss associated with bleeding compressed air.
Solution Approach 2:
The system uses the engine's own rotation to drive the flow inducer assembly, which automatically captures and directs ambient air for cooling purposes. The rotating flow inducer acts as a self-powered pump that utilizes the engine's rotational energy to supply cooling air without requiring additional energy input or compressor bleed air.
2Temperature
If compressor air is bled for cooling last stage turbine blades, then sufficient cooling is achieved, but compressor performance deteriorates
Solution Approach 1:
The invention extracts the cooling air supply function from the compressor system and replaces it with ambient air captured by the flow inducer assembly. This separation eliminates the negative impact on compressor performance while maintaining adequate cooling of the turbine blades through the rotor disk cavity system.
3Loss of energy
If ambient air is used for cooling last stage turbine blades, then engine efficiency is improved, but sufficient cooling flow is difficult to achieve
Solution Approach 1:
The invention employs a dynamic flow inducer assembly that rotates with the rotor disk, converting rotational motion into a pumping action. This dynamic mechanism actively captures ambient air and forces it through the rotor disk cavities and into the turbine blades, ensuring sufficient cooling air flow is achieved despite using lower-pressure ambient air instead of high-pressure compressor bleed air.
4Quantity of substance
If a flow inducer system is implemented to capture ambient air, then sufficient cooling flow is achieved, but device complexity increases
Solution Approach 1:
The invention merges the flow inducer assembly with the existing seal plate structure on the rotor disk. The flow inducer is integrated into the seal plate that already seals the rotor disk periphery, combining the sealing function with the new ambient air capture function. This integration minimizes additional complexity while achieving sufficient cooling air flow.
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
Enhances turbine engine efficiency by using ambient air for cooling the last stage turbine blades, providing sufficient cooling without reducing compressor performance.
Implementation Method 1
Each flow inducer assembly is configured to function as a paddle due to rotation of the rotor disk and each seal plate therewith during operation of the gas turbine engine to induce an ambient air into the disk cavity and drive it into inside of the respective turbine blade from blade root for cooling the turbine blade
Data Source
Figure 1
Figure 2~3
AI summary
The gas turbine engine includes a rotor disk (120) having circumferentially distributed disk grooves (122) and turbine blades (140). Each turbine blade (140) includes a blade root (144) inserted into the blade mounting section (124) of the disk groove (122). Seal plates (200) are attached to an aft side circumference of the rotor disk (120). The flow inducer assembly (300) is integrated to each seal plate (200) at a side facing away from the rotor disk (120). The flow inducer assembly (300) is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from the blade root for cooling the turbine blade.