PATENT CLAIM ANALYSIS

Application Number: 15750513
Application Type: Utility
Filing Date: 2018-02
Publication Date: 2018-08
Patent Classification: ["416", "09700R"]

Abstract:
A turbine airfoil ( 10 ) includes an impingement structure ( 26 A,  26 B) comprising a hollow elongated main body ( 28 ) positioned in an interior portion ( 11 ) of an airfoil body ( 12 ). The main body ( 28 ) extends lengthwise along a radial direction and defines coolant cavity ( 64 ) therewithin that receives a cooling fluid ( 60 ). The main body ( 28 ) is spaced from a pressure side wall ( 16 ) and a suction side wall ( 18 ) of the airfoil body ( 12 ) and may be spaced from an airfoil tip ( 52 ), to define respective passages ( 72, 74, 77 ) therebetween. A plurality of impingement openings ( 25 ) are formed through the main body ( 28 ) that connect the coolant cavity ( 64 ) with one or more of the respective passages ( 72, 74, 77 ). The impingement openings ( 25 ) direct the cooling fluid ( 60 ) flowing in the coolant cavity ( 64 ) to impinge on the pressure and/or suction side walls ( 16, 18 ) and/or the airfoil tip ( 52 ).

Claim (Index 17):
A turbine airfoil comprising:\n a generally hollow airfoil body formed by an outer wall extending span-wise along a radial direction, the outer wall comprising a pressure side wall and a suction side wall joined at a leading edge and a trailing edge, the airfoil body being delimited at a radially outer end by an airfoil tip, wherein a chordal axis is defined extending generally centrally between the pressure side wall and the suction side wall, and an impingement structure comprising a hollow elongated main body positioned in an interior portion of the airfoil body and extending lengthwise along the radial direction, the main body defining a coolant cavity therewithin that receives a cooling fluid, wherein the main body is spaced from the pressure side wall, the suction side wall and the airfoil tip, such that a first near wall passage is defined between the main body and the pressure side wall, a second near wall passage is defined between the main body and the suction side wall and a tip cooling passage is defined between main body and the airfoil tip, and wherein a plurality of impingement openings are formed through the main body that connect the coolant cavity with the first and second near wall passages and the tip cooling passage, for directing the cooling fluid flowing in the coolant cavity to impinge on the pressure side wall and/or suction side wall and/or the airfoil tip.

Metadata:
- Claim Count in Document: 50.0
- Percentile: 88.0
- Lexical Diversity: 2.5119
- Patent Class: 416.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: False
- Related Applications: ['15752262', '15750310', '15128492', '15833431', '15833441']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.7945108085291769
- 35 USC 102 Novelty (BERT): 0.4898337029378436
- Combined Prediction Score: 0.7640430979700437
- Mean Citation Score: 341.05394800000005
- Max Citation Score: 394.1401
- Similarity Product: 361.5212390788853

Labels:
- Claim Label 101: 1
- Claim Label 102: 0
- Claim Label 103: 1
- Claim Label 112: 1
- Combined Label: 0
- Label 101 Adjusted: 1

Dataset: test