PATENT CLAIM ANALYSIS

Application Number: 16025094
Application Type: Utility
Filing Date: 2018-07
Publication Date: 2019-02
Patent Classification: ["060", "226100"]

Abstract:
A turbofan engine according to an example of the present disclosure includes, among other things, an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

Claim (Index 30):
The turbofan engine as recited in  claim 28 , further comprising an engine intermediate case, including an engine forward mount location proximate to the gearbox and configured to support an engine mount when the engine is mounted, and an engine thrust case including an engine aft mount location configured to support an engine mount and react at least a thrust load when the engine is mounted, wherein the engine aft mount location is located between the second turbine section and the first turbine section.

Metadata:
- Claim Count in Document: 80.0
- Percentile: 95.0
- Lexical Diversity: 1.88679
- Patent Class: 60.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: False
- Related Applications: ['15292472', '15292405', '14692090', '13475252', '13599175']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.7171826063781856
- 35 USC 102 Novelty (BERT): 0.4947756005679545
- Combined Prediction Score: 0.6949419057971626
- Mean Citation Score: 333.2221100000001
- Max Citation Score: 362.86703
- Similarity Product: 336.62708746530063

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

Dataset: test