PATENT CLAIM ANALYSIS

Application Number: 15860000
Application Type: Utility
Filing Date: 2018-01
Publication Date: 2019-07
Patent Classification: ["415", "001000"]

Abstract:
The example embodiments are directed to a heat dissipation system for an electric aircraft engine. In an example, the aircraft engine includes an electric system configured to power an engine fan to provide thrust to an aircraft, the electric system including cooling channels to receive a coolant to cool one or more components of the electric system, a power source to power the electric system, and one or more guide vanes connected to the cooling channels of the electric system and configured to receive the coolant heated by and output from the cooling channels, wherein the one or more guide vanes are further to cool the heated coolant and transfer the cooled coolant back to the cooling channels of the electric system. By dissipating heat from electric system via the guide vanes, the cooling system can provide sufficient cooling without adding additional drag to the aircraft.

Claim (Index 6):
The electric aircraft engine of  claim 1 , wherein the one or more guide vanes comprise a plurality of inlet guide vanes which are positioned within an airstream of the electric aircraft engine in front of an engine fan.

Metadata:
- Claim Count in Document: 15.0
- Percentile: 86.0
- Lexical Diversity: 2.62712
- Patent Class: 415.0
- Transitional Phrase Type: none
- Component Type: 0
- Foreign Priority: False
- Related Applications: ['14957946', '15209880', '13907187', '15493623', '11595668']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.8123797347335199
- 35 USC 102 Novelty (BERT): 0.4637107208610859
- Combined Prediction Score: 0.7775128333462765
- Mean Citation Score: 213.78568600000003
- Max Citation Score: 239.71584
- Similarity Product: 147.57046892211912

Labels:
- Claim Label 101: 1
- Claim Label 102: 1
- Claim Label 103: 0
- Claim Label 112: 1
- Combined Label: 1
- Label 101 Adjusted: 1

Dataset: test