Radial Compressor Inlet Geometry for Uniform Airflow Distribution

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Solution Overview

Problem

Turboprop and turboshaft aero engines face inefficiencies due to uneven air flow distribution into the compressor, leading to turbulence and reduced performance.

Innovation Solution

A radial inlet design featuring plenums with increasing radii of curvature, a flow diverter with curvilinear sides forming a cusp, and angled sidewalls to promote uniform air distribution and reduce pressure losses.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Productivity

If conventional radial inlet design is used, then structural simplicity is maintained, but air flow distribution becomes uneven causing turbulence and reduced compressor efficiency

Engineering Contradiction:

Improvecompressor efficiencyVSAvoidinlet body structure

Core Design Contradiction:

ProductivityVSDevice complexity

Solution Approach 1:

The inlet body is segmented into multiple functional zones: plenums arranged around the inlet portion, flow diverters positioned at specific locations, and curved surfaces with varying radii of curvature. This segmentation allows each zone to perform a specific flow control function, collectively achieving uniform air distribution and eliminating turbulence while maintaining reasonable structural complexity

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent employs curved surfaces throughout the inlet body design, including plenums with curved outer surfaces, flow diverters with curved leading edges, and surfaces with varying radii of curvature. These curved geometries guide air flow smoothly around bends, prevent flow separation and turbulence, and ensure uniform distribution to the compressor inlet, directly improving compressor efficiency

Inventive Principle:

Principle #14Spheroidality (Curvature)

2Stability of the object's composition

If flow diverter with sharp edges is used, then flow direction control is achieved, but flow separation and turbulence occur reducing flow stability

Engineering Contradiction:

Improveair flow stabilityVSAvoidflow diverter geometry

Core Design Contradiction:

Stability of the object's compositionVSEase of manufacture

Solution Approach 1:

The flow diverter is designed with curved leading edges and smooth transitions instead of sharp edges. The curved geometry has a radius of curvature that is optimized to guide air flow smoothly around bends, preventing flow separation and turbulence. This curved design maintains flow stability while remaining manufacturable using standard forming processes

Inventive Principle:

Principle #14Spheroidality (Curvature)

3Productivity

If plenums with constant radius are used, then manufacturing is simplified, but uniform flow distribution cannot be achieved leading to pressure losses

Engineering Contradiction:

Improvecompressor efficiencyVSAvoidplenum geometry

Core Design Contradiction:

ProductivityVSEase of manufacture

Solution Approach 1:

The plenums are designed with varying radii of curvature along their length, with different curvature radii at different locations. This local variation in geometry is optimized to distribute air flow uniformly to different sections of the compressor inlet, preventing pressure losses and improving compressor efficiency, while remaining manufacturable using standard forming processes

Inventive Principle:

Principle #3Local quality

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 design achieves a more uniform inlet pressure profile and stable air flow, enhancing compressor efficiency and reducing turbulence and noise.

Implementation Method 1

The plenums include outer surfaces with increasing radii of curvature... The plenums are configured to direct flows from the duct around the inlet portion

Methodology Applied

Scientific EffectFlow distribution through curved surfaces:

Implementation Method 2

The flow diverter includes curvilinear sides that tangentially register with and smoothly lead to the outer surfaces of the plenums and a cusp where the curvilinear sides meet

Methodology Applied

Scientific EffectFlow guidance through curved geometry:

Data Source

PatentEP4707539A1Radial inlet compressor

Publication Date: 2026.03.11 PRATT & WHITNEY CANADA CORP

Figure 1
Figure 2A
Figure 2B

AI summary

A radial inlet body of a gas turbine engine compressor is provided. The radial inlet body includes plenums (241, 242) arranged around opposite sides of an inlet portion (210) defining a compressor inlet (215. The plenums (241, 242) include outer surfaces (2410, 2420) with increasing radii of curvature and a flow diverter. The flow diverter (250) is disposed aside the inlet portion (210) opposite a duct (220). The plenums (241, 242) are configured to direct flows from the duct (220) around the inlet portion (210). The flow diverter (250) and the plenums (241, 242) are configured to cooperatively encourage uniform distribution of the flows. The flow diverter (250) includes curvilinear sides (251, 252) that tangentially register with and smoothly lead to the outer surfaces (2410, 2420) of the plenums (241, 242) and a cusp (253) where the curvilinear sides (251, 252) meet. The radial inlet body further includes a front sidewall (261) supporting the inlet portion (210) and an aft sidewall (262) opposite the front sidewall (261). The front and aft sidewalls (261, 262) are angled toward one another along the plenums (241, 242).