PATENT CLAIM ANALYSIS

Application Number: 16056101
Application Type: Utility
Filing Date: 2018-08
Publication Date: 2018-12
Patent Classification: ["060", "805000"]

Abstract:
Methods and apparatus are provided for an axi-centrifugal compressor in a gas turbine engine for a business aviation or rotorcraft propulsion unit. The compressor includes an axial compressor section operable to affect a first pressure ratio along the flow path between a compressor inlet and a first section exit, and a centrifugal compressor section operable to affect a second pressure ratio along the flow path between a second section inlet and the compressor exit. The pressure rise across the axial and centrifugal compressor section is configured to have a tuning factor is in a range between 2.8 and 4.5 and a loading factor in a range between 0.6 and 0.8.

Claim (Index 2):
The method according to  claim 1  further comprising compressing the fluid in a plurality of axial stages along the flow path in the axial compressor section.

Metadata:
- Claim Count in Document: 11.0
- Percentile: 96.0
- Lexical Diversity: 2.11111
- Patent Class: 60.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: False
- Related Applications: ['15163990', '12404573', '13716875', '13325034', '15379935']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.7129132068144153
- 35 USC 102 Novelty (BERT): 0.4636234993938742
- Combined Prediction Score: 0.6879842360723611
- Mean Citation Score: 181.296454
- Max Citation Score: 194.13034
- Similarity Product: 150.86385307652588

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