Cable conduit for turbine engine bypass

Patent metadata

Field	Value
Publication number	US-2020347784-A1
Application number	US-202016933644-A
Country	US
Kind code	A1
Filing date	Jul 20, 2020
Priority date	Nov 8, 2017
Publication date	Nov 5, 2020
Grant date	—

Abstract

A cable conduit for a bypass flow duct may comprise a head end, a sleeve, a foot end, a boot, and a split grommet wherein the head end is coupled to the sleeve opposite the foot end, wherein the foot end comprises a flared portion, wherein the boot comprises a first flange and a neck, wherein the boot is configured to couple at the neck to the flared portion of the foot end, wherein the head end comprises a second flange and a cutout penetrating into an interior volume of the sleeve, and wherein the split grommet is coupled within the interior volume of the sleeve.

First claim

What is claimed is:

1 . A cable conduit for a bypass flow duct, comprising:
a head end, a sleeve, a foot end, a boot, and a split grommet, wherein the head end is coupled to the sleeve opposite the foot end, wherein the foot end comprises a flared portion, wherein the boot comprises a first flange and a neck, wherein the boot is configured to couple at the neck to the flared portion of the foot end, wherein the head end comprises a second flange and a cutout penetrating into an interior volume of the sleeve, and wherein the split grommet is coupled within the interior volume of the sleeve.

2 . The cable conduit of claim 1 , the sleeve includes a forward section and an aft section, wherein the sleeve comprises coupling lobes.

3 . The cable conduit of claim 2 , wherein the forward section comprises a first perforation through a forward aerodynamic surface and the aft section comprises a second perforation through an aft aerodynamic surface, wherein the first perforation and the second perforation are in fluid communication with the interior volume of the sleeve, wherein a portion of a bypass flow passes through the first perforation into the interior volume and exits the interior volume through the second perforation.

4 . The cable conduit of claim 3 , wherein the boot comprises a first half section and a second half section separable at a seamline.

5 . The cable conduit of claim 4 , wherein the boot comprises a pusher plate and a gasket.

6 . The cable conduit of claim 5 , wherein a standoff washer is embedded into the gasket.

7 . The cable conduit of claim 6 , wherein the sleeve comprises a sleeve locking feature.

8 . The cable conduit of claim 6 , wherein the split grommet comprises a mating surface comprising at least one of an extrusion, a finger, a cavity, a pocket, a bore, or an embedded stud.

9 . The cable conduit of claim 6 , wherein the gasket comprises a recessed portion configured to receive a flanged portion of the standoff washer, wherein the standoff washer defines a radial gap between the standoff washer and a gasket material.

10 . The cable conduit of claim 1 , wherein the sleeve comprises at least one of a circular cross section, an elliptical cross section, an oblate cross section, an angular cross section, a teardrop cross section, or an airfoil cross section.

11 . A gas turbine engine comprising:
a compressor section configured to compress a gas; a combustor section aft of the compressor section and configured to combust the gas; a fan section configured to produce a bypass flow; an outer case having an inner surface and an inner case having an outer surface defining a bypass flow duct there between; and a cable conduit, disposed within the bypass flow duct, comprising: a head end, a sleeve having a foot end, a boot, and a split grommet, wherein the head end is coupled to the sleeve opposite the foot end, wherein the boot comprises a first flange and a neck, wherein the neck is coupled to a flared portion of the foot end, wherein the head end comprises a second flange having and a cutout penetrating into an interior volume of the sleeve, wherein the split grommet is coupled within the interior volume of the sleeve, and wherein the second flange is coupled the inner case and the first flange is coupled to the outer case.

12 . The gas turbine engine of claim 11 , wherein the cable conduit further comprises a forward section and an aft section, wherein the sleeve comprises coupling lobes.

13 . The gas turbine engine of claim 12 , wherein the forward section comprises a first perforation through a forward aerodynamic surface and the aft section comprises a second perforation through an aft aerodynamic surface, wherein the first perforation and the second perforation are in fluid communication with the bypass flow duct and the interior volume of the sleeve, wherein a portion of the bypass flow passes through the first perforation into the interior volume and exits the interior volume through the second perforation.

14 . The gas turbine engine of claim 13 , wherein the boot comprises a first half section and a second half section separable at a seamline.

15 . The gas turbine engine of claim 14 , wherein the boot comprises a pusher plate and a gasket.

16 . The gas turbine engine of claim 15 , wherein a standoff washer is embedded into the gasket.

17 . The gas turbine engine of claim 16 , wherein the sleeve comprises a sleeve locking feature.

18 . The gas turbine engine of claim 16 , wherein the split grommet comprises a mating surface comprising at least one of an extrusion, a finger, a cavity, a pocket, a bore, or an embedded stud.

19 . The gas turbine engine of claim 16 , wherein the gasket comprises a recessed portion configured to receive a flanged portion of the standoff washer, wherein the standoff washer defines a radial gap between the standoff washer and a gasket material.

20 . A method of assembling a cable conduit in a bypass flow duct, the method comprising:
inserting a cable through an outer case and an inner case of the bypass flow duct; inserting a forward section of the cable conduit into the bypass flow duct and coupling the forward section to the inner case; inserting an aft section of the cable conduit into the bypass flow duct and coupling the aft section about the cable to the forward section; coupling the forward section to the inner case; coupling a first half section and a second half section of a boot about the cable such that the cable passes through an annular structure of a neck portion of the boot; inserting the neck portion of the boot into a flared portion of the cable conduit; and coupling the boot to the outer case.

Assignees

• Raytheon Tech Corp

Inventors

• Waitkus Christopher
• Mcauliffe Mark T
• Greenberg Randall Lee
• Dunn Colby S
• Godfrey Daniel
• Ruckey Curtis J
• Dimuzio Philip

Classifications

• F02C3/06

  the compressor comprising only axial stages (F02C3/10 takes precedence) · CPC title

• F02K3/06 Primary

  with front fan · CPC title

• F02C7/00 Primary

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• H02G3/22

  Installations of cables or lines through walls, floors or ceilings, e.g. into buildings · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title