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 8):
The component of  claim 1 , further comprising an impingement rib located within the airfoil and separating the leading edge feed cavity from the stagnation impingement cavity, wherein at least one impingement aperture is formed within the impingement rib to fluidly connect the leading edge feed cavity to the 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): 0.7984469278042025
- 35 USC 102 Novelty (BERT): 0.4801342976819736
- Combined Prediction Score: 0.7666156647919795
- Mean Citation Score: 347.918108
- Max Citation Score: 372.732
- Similarity Product: 279.6149387454987

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