PATENT CLAIM ANALYSIS

Application Number: 16018640
Application Type: Utility
Filing Date: 2018-06
Publication Date: 2018-10
Patent Classification: ["060", "226100"]

Abstract:
A gas turbine engine has a fan section including a fan, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, and a gear reduction. The low pressure compressor and the low pressure turbine have a number of blades in each of at least one of a plurality of blade rows. The blades are rotatable at least some of the time at a rotational speed in operation. The number of blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60 s≥5500 Hz, and the rotational speed is in revolutions per minute.

Claim (Index 1):
A gas turbine engine comprising:\n a fan section including a fan, and a low fan pressure ratio of less than 1.45, wherein the low fan pressure ratio is measured across a fan blade alone; a compressor section including a low pressure compressor and a high pressure compressor; wherein the fan delivers air into a bypass duct defined within a nacelle, and a portion of air into the compressor section, with a bypass ratio defined as the volume of air delivered into the bypass duct compared to the volume of air delivered into the compressor section, and the bypass ratio being greater than 10; a turbine section including a low pressure turbine and a high pressure turbine; wherein the low pressure turbine includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to the inlet as related to pressure at the outlet prior to an exhaust nozzle; a combustion section including a combustor between the high pressure compressor and the high pressure turbine; a gear reduction including an epicyclic gear train, the gear reduction positioned between the fan on one side and the low pressure turbine on another side to drive the fan at a lower speed than the low pressure turbine in operation, and the epicyclic gear train having a gear reduction ratio of greater than 2.5:1; wherein each of the low pressure compressor and the low pressure turbine includes a number of blades in each of at least one of a plurality of blade rows, the number of blades rotatable at least some of the time at a rotational speed in operation, and the number of blades in the at least one row and the rotational speed being such that the following formula holds true for the at least one row of the low pressure compressor:\n (the number of blades\u00d7the rotational speed)/60 sec\u22655500 Hz; \n the rotational speed being an approach speed in revolutions per minute, taken at an approach certification point as defined in Part  36  of the Federal Airworthiness Regulations; and wherein the gas turbine engine is rated to produce 15,000 pounds of thrust or more.

Metadata:
- Claim Count in Document: 80.0
- Percentile: 94.0
- Lexical Diversity: 2.38983
- Patent Class: 60.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: False
- Related Applications: ['15259232', '14016436', '13630276', '15014363', '14905994']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.769408936023758
- 35 USC 102 Novelty (BERT): 0.5410565229991651
- Combined Prediction Score: 0.7465736947212988
- Mean Citation Score: 397.95533600000016
- Max Citation Score: 401.15308
- Similarity Product: 308.2106683083009

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

Dataset: test