System for an inlet guide vane shroud and baffle assembly

Patent metadata

Field	Value
Publication number	US-2017191500-A1
Application number	US-201615336831-A
Country	US
Kind code	A1
Filing date	Oct 28, 2016
Priority date	Jan 4, 2016
Publication date	Jul 6, 2017
Grant date	—

Abstract

A system for an inlet guide vane shroud and baffle assembly includes a shroud. The shroud includes a first end configured to couple to an annular support member of the gas turbine engine, and a second end. The shroud also includes a distal end including an axially aft extending lip, and a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of the gas turbine engine. The shroud further includes an arcuate shroud body extending between the distal end and the second end. The shroud and baffle assembly also includes a baffle coupled to an aft side of the shroud. The baffle includes a radially outward end coupled to the aft side, a radially inward end coupled to the axially aft extending lip, and an arcuate baffle body extending there between. Both the shroud and the baffle extend circumferentially about a central axis.

First claim

What is claimed is:

1 . A shroud and baffle assembly for a gas turbine engine, the gas turbine engine including a central axis, a fan assembly positioned at a forward end, and an exhaust outlet positioned at an aft end, said shroud and baffle assembly comprising:
a shroud comprising a first end configured to couple to an annular support member of the gas turbine engine, a second end, a distal end comprising an axially aft extending lip, said distal end further comprising a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of the gas turbine engine, said shroud further comprising an arcuate shroud body extending between said distal end and said second end, wherein said shroud extends circumferentially about the central axis; and a baffle coupled to an aft side of said shroud, said baffle comprising a radially outward end coupled to said aft side, a radially inward end coupled to said axially aft extending lip, and an arcuate baffle body extending there between, wherein said baffle extends circumferentially about the central axis.

2 . The shroud and baffle assembly in accordance with claim 1 , wherein said arcuate baffle body is concave with respect to the fan assembly.

3 . The shroud and baffle assembly in accordance with claim 1 , wherein said distal end extends axially aft from a radially inward end of said arcuate shroud body.

4 . The shroud and baffle assembly in accordance with claim 1 , wherein said arcuate shroud body is concave with respect to the fan assembly.

5 . The shroud and baffle assembly in accordance with claim 1 , wherein said axially aft extending lip comprises a shroud bevel and a plurality of scallops, said shroud bevel formed on a radially inward surface of said axially aft extending lip concave with respect to the fan assembly, each scallop of said plurality of scallops comprising a cut away extending into at least a portion of said axially aft extending lip, and said radially inward surface of said axially aft extending lip and each scallop of said plurality of scallops comprising said shroud bevel.

6 . The shroud and baffle assembly according to claim 1 , wherein a radially outward surface of said shroud is configured to engage at least one inlet guide vane extending radially outward therefrom.

7 . An inlet guide vane (IGV) assembly for a gas turbine engine, the gas turbine engine including a central axis, a fan assembly positioned at a forward end, and an exhaust outlet positioned at an aft end, said IGV assembly comprising:
a shroud comprising a first end configured to couple to an annular support member of the gas turbine engine, a second end, a distal end comprising an axially aft extending lip, said distal end further comprising a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of the gas turbine engine, said shroud further comprising an arcuate shroud body extending between said distal end and said second end, wherein said shroud extends circumferentially about the central axis; and a baffle coupled to an aft side of said shroud, said baffle comprising a radially outward end coupled to said aft side, a radially inward end coupled to said axially aft extending lip, and an arcuate baffle body extending there between, wherein said baffle extends circumferentially about the central axis; and a plurality of IGVs, each IGV of said plurality of IGVs coupled to said radially outward surface, wherein said radially outward surface is configured to engage at least one IGV of said plurality of IGVs thereto, wherein said plurality of IGVs are arranged radially about the central axis.

8 . The IGV assembly in accordance with claim 7 , wherein said arcuate baffle body is concave with respect to the fan assembly.

9 . The IGV assembly in accordance with claim 7 , wherein said distal end extends axially aft from a radially inward end of said arcuate shroud body.

10 . The IGV assembly in accordance with claim 7 , wherein said arcuate shroud body is concave with respect to the fan assembly.

11 . The IGV assembly in accordance with claim 7 , wherein said axially aft extending lip comprises a shroud bevel and a plurality scallops, said shroud bevel formed on a radially inward surface of said axially aft extending lip concave with respect to the fan assembly, each scallop of said plurality of scallops comprising a cut away extending into at least a portion of said axially aft extending lip, and said radially inward surface of said axially aft extending lip and each scallop of said plurality of scallops comprising said shroud bevel.

12 . The IGV assembly according to claim 11 , wherein a radially outward surface of said shroud is configured to engage at least one inlet guide vane extending radially outward therefrom.

13 . The IGV assembly in accordance with claim 7 , wherein said second end comprises an overhang and a radially outward aft corner, said overhang extending axially aft from said radially outward aft corner.

14 . A gas turbine engine including a central axis, a fan assembly positioned at a forward end, and an exhaust outlet positioned at an aft end, said gas turbine comprising:
a core engine comprising a compressor, a combustor, and a turbine coupled in a serial flow relationship; a power engine comprising a fan and a power turbine coupled together on a common shaft, said power engine coaxial with said core engine; a shroud and baffle assembly comprising: a shroud comprising a first end configured to couple to an annular support member of the gas turbine engine, a second end, a distal end comprising an axially aft extending lip, said distal end further comprising a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of said gas turbine engine, said shroud further comprising an arcuate shroud body extending between said distal end and said second end; and a baffle coupled to an aft side of said shroud, said baffle comprising a radially outward end coupled to said aft side, a radially inward end coupled to said axially aft extending lip, and an arcuate baffle body extending there between, said baffle extending aftward into an annular space of said gas turbine engine; and a plurality of inlet guide vanes (IGVs), each IGV of said plurality of IGVs coupled radially to and between said radially outward surface and a radially inward surface of an annular housing of said compressor, wherein said shroud, said baffle, said plurality of IGVs, and said annular housing are arranged circumferentially about the central axis.

15 . The gas turbine engine in accordance with claim 14 , wherein said arcuate baffle body is concave with respect to the fan assembly.

16 . The gas turbine engine in accordance with claim 14 , wherein said distal end extends axially aft from a radially inward end of said arcuate shroud body.

17 . The gas turbine engine in accordance with claim 14 , wherein said arcuate shroud body is concave with respect to the fan assembly.

18 . The gas turbine engine in accordance with claim 14 , wherein said axially aft extending lip comprises a shroud bevel and a plurality of scallops, said shroud bevel formed on a radially inward surface of said axially aft extending lip concave with respect to the fan assembly, each scallop of said plurality of scallops comprising a cut away extending into at least a portion of said axially aft extending lip, and said radially inward surface of said axially aft extending lip and each scallop of said plurality of scallops comprising said shroud bevel.

Assignees

• Gen Electric

Inventors

• Lobocki Marcin Jacek
• Wardecki Wiktor Karol
• Kulesa Joseph Charles
• Staszewski Maciej

Classifications

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D11/00

  Preventing or minimising internal leakage of working-fluid, e.g. between stages (sealings in general F16J {; sealing arrangements for transition ducts of combustor cans F01D9/023}) · CPC title

• F01D5/082

  on the side of the rotor disc · CPC title

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F01D11/08

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title