Dual-Speed Split Compressor Gearbox Design

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Solution Overview

Problem

Conventional gas turbine engines face limitations in the rotational speed of aft stages of compressors due to tip speed constraints, leading to inefficiencies and increased losses, as increasing radius results in unacceptably small blade heights.

Innovation Solution

A dual-speed split compressor design with a gearbox that drives the forward and aft portions of the high-pressure compressor at different speeds, allowing for independent control of rotational speeds and reducing overall engine size and improving efficiency.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Speed

If the radius of aft stages is increased to increase tip speed, then the rotational speed capability is improved, but the blade height becomes unacceptably small relative to tip clearances which increases losses

Engineering Contradiction:

Improvetip speed of aft stagesVSAvoidlosses in compressor stage

Core Design Contradiction:

SpeedVSLoss of energy

Solution Approach 1:

The compressor is divided into multiple stages with different rotational speeds. The forward stages operate at one speed while the aft stages operate at a different speed, allowing each stage to be optimized independently for its specific requirements without being constrained by the radius limitations of other stages.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The compressor transitions from a single-speed rigid system to a multi-speed dynamic system where different sections can rotate at different speeds. This is achieved through the use of a gearbox that couples the turbine to the compressor sections, enabling independent speed control of forward and aft portions.

Inventive Principle:

Principle #15Dynamics

2Productivity

If a dual-speed split compressor with gearbox is implemented, then the rotational speed of compressor sections is optimized improving efficiency, but the device complexity increases

Engineering Contradiction:

Improvecompressor efficiencyVSAvoidcompressor structure

Core Design Contradiction:

ProductivityVSDevice complexity

Solution Approach 1:

A gearbox is introduced as an intermediary mechanical component between the turbine and the compressor sections. This gearbox enables the transmission of power at different speed ratios, allowing the forward and aft portions of the compressor to rotate at different speeds while being driven by a single turbine.

Inventive Principle:

Principle #24Intermediary (Mediator)

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 enhances the performance and pressure ratio capability of the compressor, reducing physical size and improving fuel burn efficiency by optimizing the rotational speed of each compressor section.

Implementation Method 1

A gas turbine engine with an improved compressor section would be useful. More specifically, a dual-speed split compressor having multiple stages rotating at different speeds for decreased compressor size and improved performance and efficiency would be particularly beneficial.

Methodology Applied

Scientific EffectMechanical Advantage: Mechanical Advantage

Data Source

PatentUS10677159B2Gas turbine engine including a dual-speed split compressor

Publication Date: 2020.06.09 GENERAL ELECTRIC CO

AI summary

A gas turbine engine includes a low pressure compressor, a high pressure compressor, a turbine, and a gearbox. The high pressure compressor includes a plurality of stages split into a forward portion and an aft portion. One or both of the forward portion and the aft portion of the high pressure compressor are driven by the turbine through a gearbox such that the forward portion and the aft portion may rotate at different speeds.