PATENT CLAIM ANALYSIS

Application Number: 15941240
Application Type: Utility
Filing Date: 2018-03
Publication Date: 2018-08
Patent Classification: ["060", "226100"]

Abstract:
A gas turbine engine includes, among other things, a fan, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to 10. A gear arrangement drives the fan. A compressor section includes both a low pressure compressor and a high pressure compressor. A turbine section drives the gear arrangement. An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor and a pressure ratio across the high pressure compressor, and greater than 50, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the high pressure compressor is greater than 7.

Claim (Index 14):
The gas turbine engine of  claim 11 , wherein:\n the pressure ratio across the low pressure compressor is less than or equal to 5, measured at sea level and at a static, full-rated takeoff power; and the overall pressure ratio is less than 80, measured at sea level and at a static, full-rated takeoff power.

Metadata:
- Claim Count in Document: 80.0
- Percentile: 90.0
- Lexical Diversity: 2.46667
- Patent Class: 60.0
- Transitional Phrase Type: none
- Component Type: 0
- Foreign Priority: False
- Related Applications: ['14964607', '13590273', '14593056', '13590399', '13418457']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.7704535406306274
- 35 USC 102 Novelty (BERT): 0.5120304476282174
- Combined Prediction Score: 0.7446112313303865
- Mean Citation Score: 311.76474599999995
- Max Citation Score: 321.2521
- Similarity Product: 202.471464742434

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

Dataset: test