17957726. CONFORMAL STRUCTURE FOR A GAS TURBINE ENGINE simplified abstract (GENERAL ELECTRIC COMPANY)
Contents
- 1 CONFORMAL STRUCTURE FOR A GAS TURBINE ENGINE
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 CONFORMAL STRUCTURE FOR A GAS TURBINE ENGINE - A simplified explanation of the abstract
- 1.4 Simplified Explanation
- 1.5 Potential Applications
- 1.6 Problems Solved
- 1.7 Benefits
- 1.8 Potential Commercial Applications
- 1.9 Possible Prior Art
- 1.10 Original Abstract Submitted
CONFORMAL STRUCTURE FOR A GAS TURBINE ENGINE
Organization Name
Inventor(s)
Constantinos Minas of Slingerlands NY (US)
William Wesley Morton of Niskayuna NY (US)
CONFORMAL STRUCTURE FOR A GAS TURBINE ENGINE - A simplified explanation of the abstract
This abstract first appeared for US patent application 17957726 titled 'CONFORMAL STRUCTURE FOR A GAS TURBINE ENGINE
Simplified Explanation
The patent application describes a gas turbine engine with a specific design for an oil tank within the nacelle, using a tank sizing factor formula to determine its dimensions.
- The gas turbine engine includes a turbomachine with compressor, combustion, and turbine sections, a fan section with a rotatable fan, a nacelle enclosing the fan, and an oil tank positioned within the nacelle.
- The oil tank's dimensions are related by a tank sizing factor formula, which is the effective length times the circumference span divided by the radial height squared.
- The tank sizing factor is between 20 and 2200, ensuring optimal sizing for the oil tank within the gas turbine engine.
Potential Applications
This technology can be applied in various gas turbine engines used in aircraft, power generation, and other industrial applications.
Problems Solved
This design helps optimize the space utilization within the nacelle of a gas turbine engine, ensuring efficient placement and sizing of the oil tank.
Benefits
- Improved efficiency in oil tank placement - Enhanced performance of the gas turbine engine - Optimal use of space within the nacelle
Potential Commercial Applications
"Optimized Oil Tank Design for Gas Turbine Engines" can find applications in aircraft manufacturing, power generation plants, and other industries requiring gas turbine engines.
Possible Prior Art
There may be prior art related to optimizing the design of components within gas turbine engines, but specific information on prior patents or innovations in oil tank sizing factors is not provided in this context.
Unanswered Questions
How does this design impact the overall weight of the gas turbine engine?
The abstract does not mention the weight implications of this specific oil tank design. Further details or testing may be needed to determine the weight impact.
Are there any potential challenges in implementing this design in existing gas turbine engines?
The abstract does not address any challenges that may arise when retrofitting or integrating this optimized oil tank design into current gas turbine engine models. Further research and development may be required to address any compatibility issues.
Original Abstract Submitted
A gas turbine engine is provided defining an axial direction, a radial direction, and a circumferential direction. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order; a fan section including a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an oil tank positioned within the nacelle, wherein the oil tank defines an effective length (L) along the axial direction, a circumference span (CS) along the circumferential direction, and a radial height (Δr) along the radial direction, and wherein these parameters are related by a tank sizing factor (TSF) equal to the effective length (L) times the circumference span (CS) divided by the radial height (Δr) squared L×CS/Δr), wherein the tank sizing factor (TSF) is between 20 and 2200.
