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 24):
A turbofan engine comprising:\n a fan including a circumferential array of fan blades; a compressor in fluid communication with the fan, the compressor including a second compressor section and a first compressor section, the second compressor section including a second compressor section inlet with a second compressor section inlet annulus area; a fan duct including a fan duct annulus area outboard of the second compressor section inlet, wherein the ratio of the fan duct annulus area to the second compressor section inlet annulus area defines a bypass area ratio that is greater than 6.0; a combustor in fluid communication with the compressor; a shaft assembly having a first portion and a second portion; a turbine in fluid communication with the combustor, the turbine having a first turbine section coupled to the first portion of the shaft assembly to drive the first compressor section, and a second turbine section coupled to the second portion of the shaft assembly to drive the fan, each of the second turbine section including blades and vanes, and a second turbine airfoil count defined as the numerical count of all of the blades and vanes in the second turbine section; and a planetary gearbox coupled to the fan and rotatable by the second turbine section through the second portion of the shaft assembly to allow the second turbine to turn faster than the fan, the gearbox having a speed reduction ratio between 2:1 and 13:1 determined by the ratio of diameters within the gearbox; wherein a ratio of the second turbine airfoil count to the bypass area ratio is less than 150; wherein the second turbine section further includes a maximum gas path radius and the fan blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.55, and wherein a hub-to-tip ratio (Ri:Ro) of the second turbine section is between 0.4 and 0.5 measured at the maximum Ro axial location in the second 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): 0.7176218850427696
- 35 USC 102 Novelty (BERT): 0.4952800343688386
- Combined Prediction Score: 0.6953876999753765
- Mean Citation Score: 333.2221100000001
- Max Citation Score: 362.86703
- Similarity Product: 310.57587574885963

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