17972720. GAS TURBINE ENGINE ACCESSORY PACKAGING simplified abstract (GENERAL ELECTRIC COMPANY)
Contents
GAS TURBINE ENGINE ACCESSORY PACKAGING
Organization Name
Inventor(s)
Daniel John Oehrle of West Chester OH (US)
Randy M. Vondrell of Newport KY (US)
GAS TURBINE ENGINE ACCESSORY PACKAGING - A simplified explanation of the abstract
This abstract first appeared for US patent application 17972720 titled 'GAS TURBINE ENGINE ACCESSORY PACKAGING
The patent application describes a gas turbine engine with specific geometric ratios and dimensions for the core cowl and combustor casing.
- The gas turbine engine has an unducted primary fan, a core engine, a combustor casing, and a core cowl.
- The core cowl has a peak cowl diameter (D) in the radial direction, while the combustor casing has a maximum combustor casing diameter (d).
- The engine has an overall core axial length (L) and an under-core cowl axial length (L).
- The core cowl diameter ratio (CDR) is between 2.7 and 3.5, and the core cowl length ratio (CLR) is between 0.25 and 0.50.
Potential Applications: - Aerospace industry for aircraft engines - Power generation for gas turbine power plants
Problems Solved: - Optimal geometric design for improved engine performance - Enhanced efficiency and fuel consumption
Benefits: - Increased engine efficiency - Reduced fuel consumption - Improved overall performance
Commercial Applications: Title: "Optimized Gas Turbine Engine for Enhanced Performance" This technology can be utilized in commercial aircraft, military jets, and power generation plants to improve efficiency and reduce operational costs.
Prior Art: No specific information provided on prior art related to this technology.
Frequently Updated Research: No information provided on frequently updated research relevant to this technology.
Questions about Gas Turbine Engine Optimization: 1. How does the core cowl diameter ratio impact engine performance? 2. What are the potential cost savings associated with using this optimized gas turbine engine design?
Original Abstract Submitted
A gas turbine engine defines an axial direction and a radial direction and comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine. The outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction. The core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L) along the axial direction. The gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L) divided by the overall core axial length (L). The CDR is between 2.7 and 3.5 and the CLR is between 0.25 and 0.50.
