Compressor Cooling for Gas Turbine Rotor Bowing
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Solution Overview
Problem
Gas turbine engines experience rotor bowing due to uneven cooling during shutdown, leading to thermal deformation and potential damage from rub-events between rotor blades and casing.
Innovation Solution
A system and method for providing cooling in the compressor section of a gas turbine engine, which includes temperature sensors to measure differential thermal gradients and activate cooling elements atop the stator to mitigate deformation by reducing temperature differences between the upper and lower portions of the rotor.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional cooling methods are used during shutdown, then the compressor section cools down, but uneven cooling causes rotor bowing and thermal deformation
Solution Approach 1:
The patent applies local quality by positioning cooling elements specifically at the upper portion of the stationary assembly to target the hottest region. Temperature sensors detect differential thermal gradients, and cooling elements are activated locally where temperature exceeds thresholds, creating non-uniform cooling distribution that counteracts rotor bowing while maintaining overall cooling effectiveness.
Solution Approach 2:
The patent implements feedback control by using temperature sensors to continuously monitor thermal gradients in the compressor section. The controller receives temperature data, compares it against predetermined thresholds, and activates cooling elements accordingly. This closed-loop system adjusts cooling based on real-time thermal conditions to prevent rotor deformation during shutdown.
2Stability of the object's composition
If cooling elements are activated to prevent rotor bowing, then thermal deformation is reduced, but device complexity increases
Solution Approach 1:
The patent applies self-service by enabling the cooling system to activate automatically based on temperature sensor feedback. The controller monitors thermal gradients and autonomously activates cooling elements when temperature thresholds are exceeded, eliminating the need for manual intervention or complex external control systems while maintaining rotor straightness.
Solution Approach 2:
The patent segments the cooling system into multiple independent cooling elements positioned at specific locations (upper portion of stationary assembly). Each cooling element can be independently controlled based on local temperature conditions, allowing targeted cooling without requiring a completely complex system-wide cooling architecture.
3Manufacturing precision
If temperature sensors and cooling elements are added, then thermal gradient control is improved, but manufacturing cost increases
Solution Approach 1:
The patent reduces manufacturing cost by implementing cooling elements only at the upper portion of the stationary assembly where thermal gradients are most problematic. Rather than uniformly distributing cooling capability throughout the entire compressor section, the system applies cooling locally where temperature sensors detect excessive heat, reducing component count and manufacturing complexity while maintaining precise thermal gradient control.
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 system effectively minimizes rotor bowing and thermal damage, improving the overall life and operation of the gas turbine engine by ensuring uniform cooling and reducing the risk of deformation during shutdown.
Implementation Method 1
cooling element positioned at the first location on the stationary assembly to cool air at the first location such that cool air moves downward due to gravity and hot air from the lower portion of the stationary assembly rises upward, wherein the cool air moving downward combines with the hot air rising upward to allow for homogenization
Implementation Method 2
cooling element positioned at the first location on the stationary assembly to cool air at the first location such that cool air moves downward due to gravity
Data Source
AI summary
A method for cooling a compressor section of a gas turbine engine includes sensing, via at least one first temperature sensor, a first temperature at the first location on a stationary assembly of the compressor section. The method also includes sensing, via at least one second temperature sensor, a second temperature at a second location on the stationary assembly of the compressor section. The second location is spaced apart from the first location. The method also includes determining, via a controller, a delta between the first temperature and the second temperature. Further, the method includes operating, via the controller, at least one cooling element when the delta exceeds a predetermined threshold, the at least one cooling element provided at the first location of the stationary assembly of the compressor section.