Jet Engine Mid-Turbine Frame Impingement Cooling

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Solution Overview

Problem

Conventional jet engine mid-turbine frames lack efficient cooling mechanisms for high-temperature intolerant components, leading to potential damage from hot gases, and existing structures do not adequately modulate cooling air flow to maintain component integrity.

Innovation Solution

An impingement structure with a radially inward and outward segment portion and a perforated structure is introduced, where cooling air impinges on the perforated structure to permeate through channels and slots, effectively cooling components by transferring heat away from the mid-turbine frame while minimizing aerodynamic resistance.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If conventional mid-turbine frame structures are used without perforated cooling mechanisms, then the structural simplicity is maintained, but the high-temperature intolerant components cannot be effectively cooled and are exposed to harmful hot gases

Engineering Contradiction:

Improvecooling effectivenessVSAvoidstructure complexity

Core Design Contradiction:

TemperatureVSDevice complexity

Solution Approach 1:

The mid-turbine frame incorporates a perforated structure with multiple holes that allow cooling air to pass through. This porous configuration enables effective cooling of high-temperature intolerant components while managing the trade-off with structural complexity. The perforated design is specifically applied to the radially outward segment portion to optimize cooling where needed.

Inventive Principle:

Principle #31Porous materials

Solution Approach 2:

The mid-turbine frame is divided into radially inward and radially outward segment portions, with the cooling function specifically implemented in the radially outward segment. This segmentation allows the cooling mechanism to be applied only where necessary, reducing overall structural complexity while improving temperature management for vulnerable components.

Inventive Principle:

Principle #1Segmentation

2Temperature

If cooling air flow is increased to improve component cooling, then heat transfer efficiency improves, but aerodynamic resistance increases

Engineering Contradiction:

Improveheat transfer efficiencyVSAvoidaerodynamic resistance

Core Design Contradiction:

TemperatureVSObject-affected harmful factors

Solution Approach 1:

The cooling function is localized to the radially outward segment portion of the mid-turbine frame, which is the area most exposed to hot gases. By concentrating cooling efforts in this specific location rather than throughout the entire frame, the design achieves effective heat transfer while minimizing the overall aerodynamic penalty of having cooling structures throughout the flow path.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The perforated structure provides sufficient cooling air flow to adequately cool the high-temperature intolerant components without excessively increasing aerodynamic resistance. The design uses just enough cooling airflow to maintain component integrity while accepting minimal impact on aerodynamic performance.

Inventive Principle:

Principle #16Partial or excessive action

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 solution enhances the cooling of high-temperature intolerant components within the mid-turbine frame, maintaining their integrity by efficiently transferring heat away from the hot gas flow path, thereby improving the operational efficiency and longevity of the jet engine components.

Implementation Method 1

effectively cooling components by transferring heat away from the mid-turbine frame

Methodology Applied

Scientific EffectHeat transfer: Conduction (thermal)

Implementation Method 2

cooling air impinges on the perforated structure to permeate through channels and slots

Methodology Applied

Scientific EffectConvection: Convection

Data Source

PatentUS10344618B2Impingement structure for jet engine mid-turbine frame

Publication Date: 2019.07.09 RTX CORP

AI summary

A mid-turbine frame (“MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine (“HPT”) and a low pressure turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.