Gas Turbine Engine Fuel Pump Layout for Reduced Frontal Projection
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current aircraft gas turbine engines have a large frontal projected area due to accessories disposed on the outer peripheral surface of the casing, which hinders size reduction without compromising engine performance.
Innovation Solution
A gas turbine engine design where a compressor, combustor, and turbine are aligned along a rotating shaft, with fuel pump units arranged circumferentially along the casing's outer surface in parallel, connected by a fuel supply pipe, allowing for reduced pump size and minimized radial projection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If accessories are disposed on the outer peripheral surface of the casing, then the engine can be driven with sufficient power output, but the frontal projected area becomes large
Solution Approach 1:
The fuel supply system is segmented into multiple fuel pump units (first fuel pump unit, second fuel pump unit, etc.) that are distributed around the outer peripheral surface of the casing. Each pump unit handles a portion of the fuel supply, allowing the system to maintain sufficient power output while reducing the frontal projected area through circumferential distribution rather than radial projection.
Solution Approach 2:
The fuel pump units are arranged in the circumferential direction around the casing rather than projecting outward in the radial direction. This dimensional repositioning moves the components from a radial layout (increasing frontal area) to a circumferential layout (maintaining compact frontal profile), effectively resolving the contradiction between power output and frontal projected area.
2Quantity of substance
If a single large fuel pump is used, then sufficient fuel supply capacity is achieved, but the radial projection increases
Solution Approach 1:
The fuel supply capacity requirement is divided among multiple fuel pump units arranged circumferentially around the casing. Each pump unit has reduced individual size compared to a single large pump, but collectively they provide sufficient fuel supply capacity. This segmentation eliminates the need for large radial projection while maintaining the required fuel throughput.
Solution Approach 2:
Multiple fuel pump units are combined through parallel connection to achieve the required total fuel supply capacity. The pumps work together to supply fuel to the combustor, merging their individual contributions to meet the overall system requirement without any single pump needing to project radially outward.
Data Source
Figure 1
Figure 2~3
Figure 4
AI summary
A gas turbine engine in which a compressor, a combustor, and a turbine are arranged so as to be lined up along a rotating shaft includes: a casing that accommodates the compressor, the combustor, and the turbine; fuel pump units that are arranged at an outside of the casing, are lined up in a circumferential direction along an outer peripheral surface of the casing, and are connected in parallel; and a fuel supply pipe that collects fuel discharged from the fuel pump units and supplies the fuel to the combustor.