Turbine Tip Clearance Control via Sloped Slide Block

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Solution Overview

Problem

Existing tip clearance control systems for turbine engines are slow to react and unable to precisely compensate for thermal/mechanical distortions, leading to inefficiencies in controlling the clearance between rotor blade tips and the blade outer air seal, particularly during cruise conditions.

Innovation Solution

A tip clearance control system that includes a base with grooves and sloped slide blocks, actuation arms, and linkages, allowing for radial translation of the blade outer air seal segments to maintain minimal gap between rotor blades and the air seal, accommodating thermal/mechanical distortions through actuator-driven movement.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Speed

If traditional passive tip clearance control systems are used, then the system structure is simple, but the reaction speed is too slow to achieve small tip clearances at engine time points of most interest

Engineering Contradiction:
Improvereaction speedVSAvoidsystem complexity
Core Design Contradiction:
SpeedVSDevice complexity

Solution Approach 1:

The patent replaces traditional pneumatic actuation systems with a purely mechanical linkage system. The actuation mechanism uses a slider-crank mechanism where a sliding block moves along a curved guide path, converting lateral motion into radial movement of the air seal. This mechanical substitution eliminates complex pneumatic components while achieving rapid response to tip clearance changes.

Inventive Principle:
Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent introduces a curved guide path that converts lateral translation motion into radial movement. The sliding block follows a predetermined curved trajectory, which automatically transforms the actuation direction (lateral) into the desired movement direction (radial) for the air seal. This dimensional transformation simplifies the mechanism while achieving the desired motion control.

Inventive Principle:
Principle #17Another dimension (Dimensionality change)

2Adaptability or versatility

If traditional tip clearance control systems are used, then the system is simpler, but they lack the ability to compensate for thermal/mechanical distortions of components

Engineering Contradiction:
Improvecompensation capabilityVSAvoidsystem complexity
Core Design Contradiction:
Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The patent creates a dynamic adjustment mechanism where the air seal position can change in real-time in response to thermal and mechanical distortions. The mechanical linkage system allows continuous adjustment of the air seal radial position, enabling the system to adapt to changing operating conditions and component distortions during engine operation.

Inventive Principle:
Principle #15Dynamics

Solution Approach 2:

The curved guide path is designed to automatically compensate for thermal and mechanical distortions without requiring external control systems. As components expand or contract due to temperature and stress changes, the mechanical linkage self-adjusts the air seal position to maintain optimal tip clearance, making the system self-regulating.

Inventive Principle:
Principle #25Self-service

3Measurement precision

If pneumatic actuation systems are used to rapidly and precisely position the air seal, then the positioning speed improves, but the system becomes very complex and costly

Engineering Contradiction:
Improvepositioning precisionVSAvoidsystem complexity
Core Design Contradiction:
Measurement precisionVSDevice complexity

Solution Approach 1:

The patent replaces complex pneumatic actuation systems with a purely mechanical linkage system. The actuation mechanism uses a slider-crank mechanism where a sliding block moves along a curved guide path, converting lateral motion into radial movement of the air seal. This mechanical substitution eliminates complex pneumatic components while achieving rapid response to tip clearance changes.

Inventive Principle:
Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent employs a simple, cost-effective mechanical linkage system instead of expensive pneumatic actuators. The mechanism uses basic mechanical components (sliding block, curved guide, linkages) that are simpler and less costly than pneumatic systems, while still achieving the required positioning precision and response speed.

Inventive Principle:
Principle #27Cheap short-living objects (Disposable)

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 reduces air leakage and maintains optimal tip clearance by allowing precise and rapid adjustment of the blade outer air seal segments, improving engine efficiency and reducing operational complexity and costs.

Implementation Method 1

A tip clearance control system includes... two sloped slide blocks... configured to convert lateral translation to radial translation

Methodology Applied
Scientific EffectMechanical Advantage: Mechanical Advantage

Data Source

PatentEP3106623B1Turbine engine tip clearance control system with lateral translatable slide block
Publication Date: 2019.08.07 UNITED TECH CORP
  • EP3106623B1 patent drawingFigure 1
  • EP3106623B1 patent drawingFigure 2
  • EP3106623B1 patent drawingFigure 3

AI summary

An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly may include a blade outer air seal segment 66, a linkage 70 and an actuation device 68. The linkage 70 may include a shaft 136 and a head 138, where the shaft 136 is connected to the blade outer air seal segment 66 and extends radially outward to the head 138. The actuation device 68 may include a sloped slide block 78 located radially within and engaged with the head 138. The actuation device 68 may be configured to laterally translate the sloped slide block 78 and thereby radially move the blade outer air seal segment 66.