PATENT CLAIM ANALYSIS

Application Number: 15884447
Application Type: Utility
Filing Date: 2018-01
Publication Date: 2019-08
Patent Classification: ["416", "09700R"]

Abstract:
Components for gas turbine engines are provided. The components include an airfoil extending between a first end and a second end and from a leading edge to a trailing edge. The airfoil has a pressure side and a suction side. The airfoil has a non-leading edge stagnation line that transitions from a location along a leading edge surface of the airfoil at the first end to a location on the airfoil on the pressure side of the airfoil at the second end. A leading edge feed cavity is located in the leading edge of the airfoil and extending between the first end and the second end of the airfoil. A stagnation impingement cavity is formed extending along a surface of the airfoil that aligns with the non-leading edge stagnation line.

Claim (Index 11):
A core assembly for forming a component of a gas turbine engine, the core assembly comprising:\n a leading edge feed cavity core arranged to form a leading edge feed cavity in a formed airfoil, the leading edge feed cavity core extending between a first end and a second end; a stagnation impingement cavity core connected to the leading edge feed cavity core and arranged to form a stagnation impingement cavity within a formed airfoil such that the formed stagnation impingement cavity aligns with a non-leading edge stagnation line, wherein a portion of the stagnation impingement cavity core is located proximate a leading edge of the formed airfoil at the first end and a portion of the stagnation impingement cavity core is located proximate a side of the formed airfoil at the second end, and at least one impingement core hole configured to form an impingement aperture fluidly connecting the formed leading edge feed cavity to the formed stagnation impingement cavity, the at least one impingement aperture formed by the respective at least one impingement core hole to enable impinging air upon an interior surface of the formed airfoil at the non-leading edge stagnation line.

Metadata:
- Claim Count in Document: 13.0
- Percentile: 86.0
- Lexical Diversity: 2.66667
- Patent Class: 416.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: False
- Related Applications: ['15791464', '15671351', '15866557', '15874070', '15368737']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.7981258949019133
- 35 USC 102 Novelty (BERT): 0.4801659218722512
- Combined Prediction Score: 0.7663298975989471
- Mean Citation Score: 347.918108
- Max Citation Score: 372.732
- Similarity Product: 298.1317292890549

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

Dataset: test