PATENT CLAIM ANALYSIS

Application Number: 16013396
Application Type: Utility
Filing Date: 2018-06
Publication Date: 2018-10
Patent Classification: ["060", "751000"]

Abstract:
A gas turbine engine includes: a plurality of combustors disposed so as to incline radially outward from a turbine side toward a compressor side; and a diffuser inner tube and outer tube forming a diffuser as an upstream portion of a path that introduces a compressed gas from the compressor to the combustors. A transition duct portion of each combustor has such a shape that a circumferential dimension thereof gradually decreases from the turbine side to the compressor side so that a circumferential gap is formed between the transition duct portions. Downstream-side portions of the diffuser inner tube and outer tube each have a shape gradually increasing in diameter toward the downstream side. A turbine-side end of the circumferential gap at an inner diameter side of the transition duct portion is positioned radially inward of an imaginary extension conical surface continuous from the diffuser inner tube.

Claim (Index 1):
A gas turbine engine in which a compressed gas from a compressor is burned and an obtained combustion gas drives a turbine, the gas turbine engine comprising:\n a plurality of combustors, each combustor having a tubular shape, being configured to burn the compressed gas from the compressor, and being positioned such that an axis thereof inclines, with respect to a rotation axis of the gas turbine engine, radially outward from a side on which the turbine is located toward a side on which the compressor is located; a diffuser outer tube forming an outer diameter side wall of a diffuser of an annular shape that forms an upstream portion of a compressed gas supply path configured to guide the compressed gas discharged from the compressor to the combustors; a diffuser inner tube disposed concentrically with the diffuser outer tube, and forming an inner diameter side wall of the diffuser; and a transition duct portion that is a portion of each combustor disposed inside a chamber forming a downstream portion of the compressed gas supply path, the transition duct portion being configured to supply the combustion gas from the combustor to the turbine, wherein the transition duct portion of each combustor has such a shape that a circumferential dimension thereof gradually decreases from the side on which the turbine is located toward the side on which the compressor is located, so that a circumferential gap is formed between adjacent transition duct portions, at least portion on a downstream side of the diffuser inner tube and at least portion on a downstream side of the diffuser outer tube have respective shapes gradually increasing in diameter toward the downstream side, and a turbine-side end of the circumferential gap at an inner diameter side of the transition duct portion is positioned radially inward of an imaginary extension conical surface extending continuously from an outer peripheral surface of the diffuser inner tube.

Metadata:
- Claim Count in Document: 13.0
- Percentile: 94.0
- Lexical Diversity: 2.17143
- Patent Class: 60.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: True
- Related Applications: ['16013042', '13408061', '11393758', '12919530', '13407987']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.7436178479166518
- 35 USC 102 Novelty (BERT): 0.5220887004229936
- Combined Prediction Score: 0.721464933167286
- Mean Citation Score: 291.67225
- Max Citation Score: 374.41336
- Similarity Product: 333.92575292506694

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