GAS TURBINE ENGINE HOLLOW FAN BLADE RIB ORIENTATION

• US 20190017386A1
• Filed: 07/14/2017
• Published: 01/17/2019
• Est. Priority Date: 07/14/2017
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Malmborg, Eric W., Weisse, Michael A.
• Granted Patent: US 10,641,098 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/16 for counteracting blade vibration
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/325 for axial flow fans blade mountings F04D29/34, blades F04D29/38
• CPC Class Codes: F04D 29/388 characterised by construction
• CPC Class Codes: F05D 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2240/301 Cross-sectional characteristics
• CPC Class Codes: F05D 2250/131 polygonal
• CPC Class Codes: F05D 2250/18 patterned
• CPC Class Codes: F05D 2250/38 angled, e.g. sweep angle
• CPC Class Codes: F05D 2260/941 particularly aimed at mechanical or thermal stress reduction
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: F05D 2300/173 Aluminium alloys, e.g. AlCuMgPb
• CPC Class Codes: F05D 2300/174 Titanium alloys, e.g. TiAl
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A fan blade includes first and second portions that are secured to one another and provide a cavity. The first and second portions form an exterior airfoil surface that extends in a radial direction from a root to a tip and in a chord-wise direction from a leading edge to a trailing edge. Radial ribs extend in a radial direction from the root toward the tip and are spaced apart from one another in the chord-wise direction. First and second angled ribs intersect one another at a first apex. The radial ribs intersect at least one of the first and second angled ribs. The first and second angled ribs are at an angle relative to one of the radial ribs. The angle is in a range of 45°+/−30°.

Claims