# US 12,006,026 B2 · Sound-reducing rotor blade tracking wedge profile

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- Number: US 12,006,026 B2
- Document ID: US12006026B2
- Status: Granted
- Kind: B2
- Application number: 17/369,238
- Filed: 2021-07-07
- Published: 2022-01-13
- Granted: 2024-06-11
- Earliest claimed: 2020-07-10
- Assignees: Haymatt, L.L.C.
- Applicants: Robert T. Loftus
- Inventors: Robert T. Loftus
- Web page: https://patentgrep.com/patent/US12006026B2

## CPC

- B64C 27/008: {Rotors tracking or balancing devices}
- B64C 27/467: Aerodynamic features
- B64C: AEROPLANES; HELICOPTERS

## Abstract

This invention provides convenient airframe vibration, tracking, and acoustic improvements of a helicopter rotor blade by use of a profile system. The profile system is designed to minimize acoustic disturbances as air passes the airfoil. The profile may be attached through an adhesive system that allows convenient removal and relocation for use by the helicopter manufacturer or by the helicopter operator in a field environment.

## Claims

### Claim 1

A method for reducing airframe vibration, improving blade tracking, and reducing undesirable acoustic effects of a helicopter rotor blade, said method comprising the steps of:
a) selecting a profile shape having a trailing edge trailing curvature set between a trailing side corner and a trailing corner so that a trailing edge of the profile shape modifies the flow pattern at the trailing end of a rotor blade;
b) applying an attachable profile of the selected profile shape to either an upper or lower surface of the rotor blade so that the attachable profile extends rearward beyond a trailing end of the rotor blade;
c) routing downstream velocity and vortex shedding of the attachable profile; and
d) modifying flow characteristics in a separating shear layer to reduce vortex shedding noise and to alter a frequency of flow instabilities from audible to inaudible frequencies.

### Claim 2 (depends on 1)

The method as set forth in claim 1 further including the step of adhering the attachable profile to the trailing end of the rotor blade.

### Claim 3 (depends on 1)

The method as set forth in claim 1 wherein said step of applying comprises applying the attachable profile to the upper surface of the rotor blade.

### Claim 4 (depends on 1)

The method of claim 1 where the attachable profile is permanently attached to the airfoil.

### Claim 5 (depends on 1)

The method of claim 1 where the attachable profile is detachably attached to the airfoil for the purpose of future removal.

### Claim 6 (depends on 1)

The method as set forth in claim 1 wherein said step of applying comprises applying the attachable profile to the lower surface of the rotor blade.