Single row vane assembly for a thrust reverser

Patent metadata

Field	Value
Publication number	US-10648426-B2
Application number	US-201614995396-A
Country	US
Kind code	B2
Filing date	Jan 14, 2016
Priority date	Jan 14, 2016
Publication date	May 12, 2020
Grant date	May 12, 2020

Abstract

A thrust reverser system comprising a single row vane assembly is provided. The provided thrust reverser system is capable of meeting performance requirements for turbine engines with reduced weight and cost.

First claim

What is claimed is:

1. A thrust reverser system for a turbine engine comprising a nacelle surrounding the engine, the thrust reverser system comprising:
a support structure configured to be mounted to the engine;
a transcowl mounted on the support structure and forming a portion of the nacelle, the transcowl movable between a first position, in which a front edge of the transcowl abuts the support structure, and a second position, in which the front edge of the transcowl is moved aft of the support structure by an aperture length that is measured from an aft end of an outer surface of the support structure to an outer surface of the front edge of the transcowl, forming an aperture between the front edge and the support structure, the aperture extending circumferentially around an engine centerline; and
wherein the outer surface of the support structure and the outer surface of the front edge of the transcowl form an outer flow surface of the engine when the transcowl is in the first position; and
a single row vane assembly circumferentially disposed within the aperture, and coaxial with the engine centerline, the single row vane assembly configured such that any imaginary line drawn parallel with the engine centerline through the aperture intersects at most one vane, the vane comprising a knee, a first vane leading edge, and a first vane trailing edge;
the knee of the vane is located on a plane that is perpendicular to a thrust reverser centerline, the first vane leading edge extends forward from the knee at an angle alpha, the first vane trailing edge extends forward from the knee at an angle beta; and
a forward-most portion of the first vane trailing edge is a first distance from the aft end of the outer surface of the support structure, measured parallel to the engine centerline, the first distance being less than or equal to half the aperture length.

2. The thrust reverser system of claim 1 , comprising a blocking assembly mounted within the transcowl and configured to direct engine airflow to discharge through the aperture, to thereby generate reverse thrust, when the transcowl is in the second position.

3. The thrust reverser system of claim 2 , wherein a ratio of the first distance to the aperture length is a first predetermined ratio.

4. The thrust reverser system of claim 3 , wherein the first predetermined ratio is within the range of 0.3 to 0.5.

5. A turbine engine, comprising:
a thrust reverser system, comprising a support structure configured to be mounted to the engine;
a transcowl mounted on the support structure and comprising a front edge, the transcowl movable between a first position, in which the front edge abuts the support structure, and a second position, in which the front edge is moved aft of the support structure by an aperture length that is measured from an aft end of an outer surface of the support structure to an outer surface of the front edge of the transcowl, forming an aperture that extends circumferentially around an engine centerline;
wherein the outer surface of the support structure and the outer surface of the front edge of the transcowl form an outer flow surface of the engine when the transcowl is in the first position; and
a blocking assembly mounted within the transcowl and configured to direct engine airflow to discharge through the aperture, to thereby generate reverse thrust, when the transcowl is in the second position; and
a single row vane assembly circumferentially disposed within the aperture, and coaxial with an engine centerline, the single row vane assembly configured such that any imaginary line drawn parallel with the engine centerline through the aperture intersects at most one vane, the vane having a knee, a vane leading edge and a vane trailing edge;
the knee of the vane is located on a plane that is perpendicular to a thrust reverser centerline, the first vane leading edge extends forward from the knee at an angle alpha, the first vane trailing edge extends forward from the knee at an angle beta; and
a forward-most portion of the first vane trailing edge is a first distance from the aft end of the outer surface of the support structure, measured parallel to the engine centerline, the first distance being less than the aperture length; and
wherein the first distance is less than half of the aperture length.

6. The turbine engine of claim 5 , wherein a ratio of the first distance to the aperture length is greater than 0.3 and less than 0.5 and further comprising one or more side beams (i) coupled to the support structure, and (ii) extending aft therefrom, and wherein the vane is mounted between two side beams of the one or more side beams.

Assignees

• Honeywell Int Inc

Inventors

• Smith Danis Burton
• Knowles Mark
• Alstad Shawn
• Romano Robert
• Pearson John Taylor
• Anderson Morris
• Robinson David

Classifications

• F05D2240/129

  Cascades, i.e. assemblies of similar profiles acting in parallel · CPC title

• F02K1/625 Primary

  the aft end of the engine cowling being movable to uncover openings for the reversed flow · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F02K1/72

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title