PATENT CLAIM ANALYSIS

Application Number: 15881240
Application Type: Utility
Filing Date: 2018-01
Publication Date: 2018-05
Patent Classification: ["060", "226100"]

Abstract:
A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.

Claim (Index 19):
The gas turbine engine as set forth in  claim 18 , wherein a power ratio of a flat-rated Sea Level Take-Off thrust provided by said engine in lbf, to a volume of a turbine section including both said high pressure turbine section and low pressure turbine section in inch 3  being greater than or equal to 4.0 lbf/inch 3 .

Metadata:
- Claim Count in Document: 80.0
- Percentile: 86.0
- Lexical Diversity: 2.0678
- Patent Class: 60.0
- Transitional Phrase Type: none
- Component Type: 0
- Foreign Priority: False
- Related Applications: ['15484441', '13908177', '13974136', '14260557', '14859381']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.8136415759983648
- 35 USC 102 Novelty (BERT): 0.6052577101139497
- Combined Prediction Score: 0.7928031894099233
- Mean Citation Score: 468.870238
- Max Citation Score: 491.59018
- Similarity Product: 443.8228919350242

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