Gas Turbine Blade Outer Air Seal Segmented Mounting

Resolve Bottlenecks,
Find Innovative Solutions
Generate Solutions

Solution Overview

Problem

Existing blade outer air seal assemblies for gas turbine engines face challenges in ensuring effective sealing and reducing stress on ceramic matrix composite (CMC) components, which can lead to increased metallic interface temperatures and radiant heat loads.

Innovation Solution

A blade outer air seal assembly featuring a platform engaged with hooks and a pin system, where the pin has varying diameters for secure engagement with the carrier, and scallops for three-point contact, reduces stress and allows for active cooling of the support structure, using ceramic and metallic materials for enhanced durability and thermal management.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If a blade outer air seal assembly is used to ensure effective sealing, then sealing performance is improved, but stress on ceramic matrix composite components increases leading to higher metallic interface temperatures

Engineering Contradiction:
Improvesealing performanceVSAvoidmetallic interface temperature
Core Design Contradiction:
ReliabilityVSTemperature

Solution Approach 1:

The air seal assembly is divided into multiple seal segments that can be independently positioned and stressed. This segmentation distributes the thermal and mechanical loads across multiple interfaces rather than concentrating stress on a single continuous seal, thereby reducing peak temperatures at metallic interfaces while maintaining overall sealing effectiveness.

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

A carrier structure serves as an intermediary between the ceramic matrix composite seal segments and the metallic turbine components. This carrier acts as a thermal and mechanical buffer, isolating the CMC segments from direct thermal contact with metallic interfaces, thus reducing heat transfer and interface temperatures while still enabling effective sealing.

Inventive Principle:
Principle #24Intermediary (Mediator)

2Strength

If ceramic matrix composite materials are used for blade outer air seals, then durability and thermal resistance are improved, but stress concentration occurs leading to increased metallic interface temperatures

Engineering Contradiction:
Improvethermal resistanceVSAvoidmetallic interface temperature
Core Design Contradiction:
StrengthVSTemperature

Solution Approach 1:

The seal segments are designed with non-uniform thickness and varying material properties across different regions. The local geometry and material composition are optimized to distribute stress more evenly, preventing stress concentration at specific points that would otherwise lead to elevated metallic interface temperatures while maintaining high thermal resistance where needed.

Inventive Principle:
Principle #3Local quality

Solution Approach 2:

The seal segments are designed to accommodate thermal expansion and contraction dynamically. By allowing the CMC segments to expand and contract independently within their mounting structure, the design prevents stress concentration that would occur with rigid constraints, thereby reducing heat transfer to metallic interfaces while maintaining the high thermal resistance of the ceramic material.

Inventive Principle:
Principle #15Dynamics

Data Source

PatentEP3739168B1Gas turbine BOAS assembly and method
Publication Date: 2023.06.28 RTX CORP
  • EP3739168B1 patent drawingFigure 1
  • EP3739168B1 patent drawingFigure 2
  • EP3739168B1 patent drawingFigure 3~4

AI summary

A blade outer air seal assembly (104) includes a support structure (110). A blade outer air seal (106) has a plurality of segments (105) that extend circumferentially about an axis (A) and mounted in the support structure (110) via a carrier (112; 212). At least one of the plurality of segments (105) has a base portion (124) that extends between a first circumferential side (C1) and a second circumferential side (C2) and from a first axial side (Al) to a second axial side (A2). A first hook (127) extends from the base portion (124) near the first axial side (Al) and faces towards the second axial side (A2). A second hook (126) extends from the base portion (124) near the second axial side (A2) and faces towards the first axial side (Al). A slot (138) is in the second hook (126) configured to receive a pin (150).