Flexible ducting system including an articulable sealed joint

• US 7,600,711 B1
• Filed: 05/16/2006
• Issued: 10/13/2009
• Est. Priority Date: 05/16/2006
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Nyhus, Daniel A.
• Primary Examiner(s): Carone; Michael
• Assistant Examiner(s): Sanderson; Joseph W
• Application Number:
  US11/434,676
• Publication Number:
  US 20090250548A1
• Time in Patent Office: 1,246 Days
• Field of Search: 244/6, 244/7.A, 244/8, 244/17.11, 137/561.A, 137872-876
• US Class Current: 244/7.00A
• CPC Class Codes: B64C 27/18 the means being jet-reaction apparatus
• CPC Class Codes: B64C 3/385 Variable incidence wings
• CPC Class Codes: F16B 2200/50 Flanged connections
• CPC Class Codes: F16L 27/1012 Flanged joints
• CPC Class Codes: Y10T 137/85938 Non-valved flow dividers

Abstract

Aircraft including a powerplant mounted on an airframe and a rotor/wing rotatably mounted on the airframe. The rotor/wing has multiple blades extending outward from roots adjacent the airframe to tips opposite the roots and having internal conduits extending between inlets adjacent the roots and downstream outlets. The aircraft also includes multiple intermediate ducts having upstream ends including flanges and downstream ends slidably and pivotally connected to corresponding blade inlets. Moreover, the aircraft includes a manifold having an upstream end in fluid communication with the powerplant and multiple downstream ends including flanges connected to upstream ends of corresponding intermediate ducts. The aircraft further includes multiple covers connected to corresponding manifold flanges and covering corresponding intermediate duct flanges. The aircraft also includes multiple absorbers positioned between corresponding intermediate duct flanges and manifold flanges and between the intermediate duct flanges and corresponding covers to control movement of the intermediate duct flanges.

Claims

1. An aircraft comprising:

an airframe having a fuselage extending longitudinally between a forward end and an aft end opposite the forward end and a set of fixed wings extending laterally from the fuselage;

a power plant mounted on the airframe producing exhaust during operation of the aircraft for powering the aircraft;

a rotor/wing assembly rotatably mounted on the airframe for selective rotation with respect to the airframe, said rotor/wing assembly having a plurality of blades, each blade of said plurality of blades extending outward from a root adjacent the airframe to a tip opposite the root and having an internal conduit extending through the blade between an inlet adjacent the root of the blade and an outlet downstream from the inlet;

a plurality of intermediate ducts, each intermediate duct of said plurality of intermediate ducts having an upstream end including a flange and a downstream end downstream from the upstream end slidably and pivotally connected to the inlet of a corresponding blade of said plurality of blades of the rotor/wing assembly;

a manifold having an upstream end in fluid communication with the power plant and a plurality of downstream ends, each downstream end of said plurality of downstream ends of the manifold including a flange connected to an upstream end of a corresponding intermediate duct of said plurality of intermediate ducts for directing exhaust received by the manifold to the intermediate duct;

a plurality of covers, each cover of said plurality of covers being connected to one of said manifold flanges and covering a corresponding one of said intermediate duct flanges; and

a plurality of absorbers, each absorber of said plurality of absorbers being positioned between one of the intermediate duct flanges and a corresponding one of said manifold flanges and extending between the intermediate duct flange and said cover covering the intermediate duct flange to allow limited movement of said intermediate duct flange with respect to said manifold flange and the cover.

2. The aircraft as set forth in claim 1 further comprising a plurality of gaskets, each gasket of said plurality of gaskets being positioned between one of said manifold flanges and a corresponding absorber and between said manifold flange and a corresponding intermediate duct flange.

3. The aircraft as set forth in claim 2 wherein each gasket includes an extension extending between the corresponding manifold flange and a corresponding cover of said plurality of covers.

4. The aircraft as set forth in claim 2 wherein each gasket has a lateral surface and the corresponding intermediate duct has an inner surface opposite said lateral surface and the gasket includes a protrusion extending from its lateral surface toward said inner surface to reduce a potential for exhaust passing between the gasket and the intermediate duct during operation of the aircraft.

5. The aircraft as set forth in claim 2 wherein:

each intermediate duct has an inboard edge that is spaced from the intermediate duct flange;

each intermediate duct includes a longitudinal rib positioned between said intermediate duct flange and said inboard edge; and

each gasket includes a slot for receiving the longitudinal rib of a corresponding intermediate duct.

6. The aircraft as set forth in claim 5 wherein:

each intermediate duct is pivotable between a default position and a plurality of pivoted positions; and

said longitudinal rib of each intermediate duct in its default position is spaced from a bottom of said corresponding gasket slot.

7. The aircraft as set forth in claim 1 wherein each of said intermediate ducts is pivotable with respect to the manifold during operation of the aircraft.

8. The aircraft as set forth in claim 1 wherein each absorber comprises an elastomeric material.

9. The aircraft as set forth in claim 1 wherein each absorber includes an inboard wave spring positioned between the respective manifold flange and the intermediate duct flange and an outboard wave spring positioned between said intermediate duct flange and said corresponding cover.

10. The aircraft as set forth in claim 1 wherein each downstream end of the intermediate duct includes a toroidal or spherical portion slidable and pivotable with respect to the inlet of the corresponding blade of said plurality of blades of the rotor/wing assembly.

11. The aircraft as set forth in claim 1 further comprising a plurality of connectors, each of said connectors connecting one of said covers to a corresponding one of said manifold flanges.

12. The aircraft as set forth in claim 11 wherein each connector includes a v-band clamp.