Integrated Axial Compressor Diffuser and Turbine Vane Assembly

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Current gas turbine engine designs face challenges in reducing the axial length of the engine core while maintaining efficient cooling and combustion processes, particularly due to the need for bleed cooling which diverts air from the compressor section to cool the turbine vanes, reducing the air available for combustion.

Innovation Solution

The proposed solution involves rearranging the compressor and combustor sections, where a compressor diffuser is integrated with the high-pressure turbine blade assembly, allowing compressed air to flow radially outward through the internal vane path of the turbine vanes for cooling and then surround the combustor for combustion, thereby eliminating the need for bleed cooling.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If bleed cooling flow is diverted from the compressor section to cool the turbine vanes, then the turbine vane cooling is improved, but the amount of air available for combustion in the combustor is reduced

Engineering Contradiction:

Improveturbine vane coolingVSAvoidair available for combustion

Core Design Contradiction:

TemperatureVSQuantity of substance

Solution Approach 1:

The patent combines the compressor diffuser with the turbine vane assembly into a single integrated component. The compressor diffuser is positioned within the turbine vane structure, allowing compressed air to flow directly through the turbine vanes for cooling without requiring separate bleed cooling pathways. This integration eliminates the need to divert air from the combustor, as the compressed air serves dual purposes: compression/diffusion and turbine vane cooling.

Inventive Principle:

Principle #5Merging (Combining)

2Length of moving object

If the axial length of the engine core is reduced by rearranging compressor and combustor sections, then the engine size and weight are reduced, but the conventional airflow path and cooling arrangement become more difficult to implement

Engineering Contradiction:

Improveaxial length of engine coreVSAvoidairflow path arrangement

Core Design Contradiction:

Length of moving objectVSDevice complexity

Solution Approach 1:

The patent transitions from a conventional axial airflow arrangement to a radial airflow configuration. The compressor diffuser directs air radially outward through the turbine vanes instead of maintaining purely axial flow. This dimensional change in airflow direction enables the compressor and combustor to be positioned at the same axial level with the compressor radially inward from the combustor, thereby reducing the axial length of the engine core while maintaining effective cooling pathways.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

Solution Approach 2:

The compressor diffuser is nested within the turbine vane assembly structure. The diffuser is positioned inside the radial span of the turbine vanes, with the diffuser outlet directing air through the internal passages of the turbine vanes. This nested arrangement allows both components to occupy overlapping spatial volumes, enabling compact engine core design with reduced axial length.

Inventive Principle:

Principle #7Nested doll (Nesting)

3Quantity of substance

If a larger compressor is used to provide sufficient cooling air, then the cooling capacity is improved, but the engine size and core flow requirements increase

Engineering Contradiction:

Improvecooling air capacityVSAvoidengine size

Core Design Contradiction:

Quantity of substanceVSWeight of moving object

Solution Approach 1:

The compressor and its diffuser serve multiple functions simultaneously: they compress the incoming air, diffuse it to reduce velocity and increase pressure, and directly provide cooling air to the turbine vanes through the integrated diffuser-vane structure. This multi-functionality eliminates the need for separate bleed cooling systems and larger compressor capacity, as the same compressed air performs both propulsion and cooling roles.

Inventive Principle:

Principle #6Universality (Multi-functionality)

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

This configuration reduces the axial length of the engine core, improves cooling efficiency by directly cooling the turbine vanes, and enhances combustion efficiency by using cooled air for combustion, potentially increasing fuel efficiency and reducing weight and complexity.

Implementation Method 1

compressed air to flow radially outward through the internal vane path of the turbine vanes

Methodology Applied

Scientific EffectRadial flow:

Implementation Method 2

compressor diffuser is arranged to direct the core flow from the compressor section

Methodology Applied

Scientific EffectDiffusion: Diffusion

Data Source

PatentUS12338748B1Integrated axial compressor diffuser and high pressure turbine vane assembly

Publication Date: 2025.06.24 PRATT & WHITNEY CANADA CORP

AI summary

Gas turbine engines include a compressor section configured to compress a core flow and a combustor section having a combustor that is arranged downstream from the compressor section along a path of the core flow. A turbine section is arranged downstream from the combustor along the path of the core flow, and includes a plurality of first vanes arranged at an outlet of the combustor, with at least one first vane of the plurality of first vanes having an internal vane path. A compressor diffuser is arranged to direct the core flow from the compressor section through the internal vane path. The path of the core flow, in a flow direction, passes through the compressor section, the compressor diffuser, the internal vane path, the combustor, and then between the first vanes of the plurality of first vanes to enter the turbine section.