Engine inlet duct installation

Patent metadata

Field	Value
Publication number	US-9708979-B2
Application number	US-201314088539-A
Country	US
Kind code	B2
Filing date	Nov 25, 2013
Priority date	Nov 25, 2013
Publication date	Jul 18, 2017
Grant date	Jul 18, 2017

Abstract

A method of securing two components to each other includes locating a mounting strip at a first mounting flange of a first component. The mounting strip is slidably affixed to the first component and includes a plurality of strip openings and a tightening ramp located at each strip opening of the plurality of strip openings. A second component is located such that a second mounting flange of the second component abuts the first mounting flange. A plurality of fasteners are located at the second mounting flange. A fastener of the plurality of fasteners extends through each strip opening of the plurality of strip openings. The mounting strip is slid in a direction to increase tension on the plurality of fasteners via an increasing height of the tightening ramp under a fastener head of the fastener, thereby securing the first mounting flange to the second mounting flange.

First claim

What is claimed is:

1. An inlet duct assembly comprising an inlet duct having a bifurcated configuration along a longitudinal axis thereof and comprising:
a first inlet duct leg comprising a pair of first flanges extending along opposing longitudinal edges thereof, each first flange including:
a first mounting flange; and
a plurality of fasteners extending from the first mounting flange, each fastener having a fastener head disposed at a preselected distance from the mounting flange;
a second inlet duct leg comprising a pair of second flanges extending along opposing longitudinal edges thereof, each second flange including:
a second mounting flange configured to abut a respective one of the first mounting flanges and comprising a plurality of fastener openings receiving the fasteners therethrough; and
a mounting strip moveably located on the second mounting flange having:
a plurality of strip openings, a respective one of the fasteners extending therethrough each strip opening; and
a tightening ramp corresponding to each strip opening having an increasing height in one direction;
the first and second inlet duct legs configured to extend along lateral sides of an engine axis and around a mount shaft located at the engine axis:
wherein movement between the mounting strips and the fastener heads in an axial direction of the mounting strips increases a tension on the fasteners and thus secures the first mounting flanges to the second mounting flanges.

2. The inlet duct assembly of claim 1 , wherein each mounting strip is slidably located on the respective second mounting flange, the inlet duct assembly further comprising:
a tightening bolt extending from one end of each mounting strip;
a stop disposed at each second mounting flange; and
a tightening nut disposed at each stop, such that tightening the tightening nut over the tightening bolt urges sliding of the mounting strip toward the stop.

3. The inlet duct assembly of claim 2 , wherein each tightening ramp has increasing height with distance from the stop.

4. The inlet duct assembly of claim 1 , wherein each mounting strip is slidably located on the respective second mounting flange and sliding the mounting strip increases a height of tightening of the tightening ramps between the fastener heads and the second mounting flange.

5. The inlet duct assembly of claim 1 , wherein each fastener is one of a bolt, screw or pin.

6. The inlet duct assembly of claim 1 , wherein the first inlet duct leg and/or the second duct leg are secured to an airframe.

7. The inlet duct assembly of claim 1 , wherein each strip opening has a keyhole shape.

8. The inlet duct assembly of claim 1 , wherein each fastener head is slidable along the corresponding ramp.

9. A method of installing an inlet duct assembly comprising an inlet duct having a bifurcated configuration along a longitudinal axis thereof to a rotary winged aircraft comprising:
locating a first inlet duct leg at an engine inlet of a rotary winged aircraft, the first inlet duct leg comprising a pair of first flanges extending along opposing longitudinal edges thereof, each first flange including:
a first mounting flange; and
a plurality of fasteners extending from the first mounting flange, each fastener having a fastener head disposed at a preselected distance from the mounting flange;
locating a second inlet duct leg at the engine inlet, the second inlet duct leg comprising a pair of second flanges extending along opposing longitudinal edges thereof, each second flange including a second mounting flange which abuts a respective one of the first mounting flanges and comprises a plurality of fastener openings receiving the fasteners therethrough, each second flange including a mounting strip moveably located on the second mounting flange having:
a plurality of strip openings, a respective one of the fasteners extending therethrough each strip opening; and
a tightening ramp corresponding to each strip opening having an increasing height in one direction; and
moving the mounting strips and the fastener heads relative to each other in an axial direction of the mounting strips to increase tension on the fasteners thereby securing the second mounting flanges to the first mounting flanges;
wherein the first and second inlet duct legs extend along lateral sides of an engine axis and around a mount shaft located at the engine axis.

10. The method of claim 9 , wherein each mounting strip is slidable on the respective second mounting flange, and moving the mounting strip and the fastener heads relative to each other in the axial direction of the mounting strip includes sliding the mounting strip and comprises:
extending a tightening bolt of the mounting bracket strip through a stop; and
tightening a nut disposed at the stop over the bolt to urge the mounting bracket strip toward the stop.

11. The method of claim 9 , wherein moving each mounting strip and the fastener heads relative to each other increases a tightening ramp height between each fastener head and the respective second mounting flange to increase the tension on the fasteners.

12. The method of claim 9 , wherein each fastener is one of a bolt, screw or pin.

13. The method of claim 9 , wherein the first inlet duct leg and/or the second inlet duct leg are secured to an airframe.

14. The method of claim 9 , wherein each strip opening has a keyhole shape.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Chasen Scott A

Classifications

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F05D2220/329

  in helicopters · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• F16B21/09

  Releasable fastening devices with a stud engaging a keyhole slot · CPC title