PATENT CLAIM ANALYSIS

Application Number: 16188283
Application Type: Utility
Filing Date: 2018-11
Publication Date: 2019-03
Patent Classification: ["060", "226100"]

Abstract:
An aerospace turbofan engine that injects oxygen-enriched gas from an inlet includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a first afterburner outer ring. An aerospace turbofan engine that injects oxygen-enriched gas from an inlet and an afterburner individually or simultaneously includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a second afterburner outer ring. The aerospace turbofan engines which fully utilize oxygen in the atmosphere for combustion and work in various flight altitude ranges adopt regenerative cooling-type afterburners with acoustic cavity and baffle plates, so that an aircraft can fly to an altitude of 20-50 km and reach a speed of Mach 2-5. Variants of the aerospace turbofan engines are disclosed.

Claim (Index 9):
The aerospace turbofan engine of  claim 1 , wherein\n the spiral groove outer wall upon entire processing is sectioned longitudinally into two symmetrical halves; and the two symmetrical halves are welded into a whole when the two symmetrical halves are fitted in the spiral groove inner wall.

Metadata:
- Claim Count in Document: 38.0
- Percentile: 98.0
- Lexical Diversity: 1.88571
- Patent Class: 60.0
- Transitional Phrase Type: none
- Component Type: 0
- Foreign Priority: True
- Related Applications: ['11209918', '10797212', '10848986', '11095647', '10360016']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.7125401739509543
- 35 USC 102 Novelty (BERT): 0.4960091485622468
- Combined Prediction Score: 0.6908870714120835
- Mean Citation Score: 219.36225
- Max Citation Score: 230.01659
- Similarity Product: 154.0649025361991

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