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 13):
The core assembly of  claim 11 , further comprising at least one impingement aperture core arranged to form a respective impingement aperture in the formed airfoil to fluidly connect the formed leading edge feed cavity to the formed stagnation impingement cavity.

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): 0.7988169870992692
- 35 USC 102 Novelty (BERT): 0.4800978394357992
- Combined Prediction Score: 0.7669450723329222
- Mean Citation Score: 347.918108
- Max Citation Score: 372.732
- Similarity Product: 258.24205409646044

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