Low loss baffled serpentine turns

Patent metadata

Field	Value
Publication number	US-2016376897-A1
Application number	US-201514752143-A
Country	US
Kind code	A1
Filing date	Jun 26, 2015
Priority date	Jun 26, 2015
Publication date	Dec 29, 2016
Grant date	—

Abstract

A vane includes a forward rib and an aft rib positioned axially aft of the forward rib. The vane also includes a middle rib positioned axially between the forward rib and the aft rib, such that the forward rib and the middle rib define a forward passage configured to receive a forward baffle and the middle rib and the aft rib define an aft passage configured to receive an aft baffle. The vane also includes an inner surface extending axially from the forward rib to the aft rib, being radially separated from the middle rib via a gap such that air can flow between the aft passage and the forward passage via the gap, and having a radially outward curve from the forward rib to the middle rib and having a radially inward curve from the middle rib to the aft rib.

First claim

1 . A vane for use in a gas turbine engine, the vane comprising:
a forward rib and an aft rib positioned axially aft of the forward rib; a middle rib positioned axially between the forward rib and the aft rib, such that the forward rib and the middle rib define a forward passage configured to receive a forward baffle and the middle rib and the aft rib define an aft passage configured to receive an aft baffle; and an inner surface extending axially from the forward rib to the aft rib, being radially separated from the middle rib via a gap such that air can flow between the aft passage and the forward passage via the gap, and having a radially outward curve from the forward rib to the middle rib and having a radially inward curve from the middle rib to the aft rib.

2 . The vane of claim 1 , wherein in response to the forward passage receiving the forward baffle and the aft passage receiving the aft baffle, air may flow between the aft passage and the forward passage on a circumferential side of at least one of the aft baffle or the forward baffle.

3 . The vane of claim 1 , wherein the radially outward curve and the radially inward curve are positioned at an outer diameter edge of the vane.

4 . The vane of claim 1 , wherein the vane further defines two passages forward of the forward rib and two passages aft of the aft rib.

5 . The vane of claim 1 , further comprising a collar extending radially outward from the inner surface, wherein in response to the forward passage receiving the forward baffle, the collar is positioned adjacent the forward baffle on a circumferential side of the forward baffle.

6 . The vane of claim 5 , wherein the collar is configured to be coupled to the forward baffle via welding.

7 . The vane of claim 1 , further comprising the forward baffle and the aft baffle, wherein the forward baffle and the aft baffle overlap at a location radially outward from the middle rib.

8 . The vane of claim 7 , wherein the forward baffle includes a first circumferential side and a second circumferential side defining a slot at an aft end of the forward baffle and the aft baffle includes a forward tapered end configured to be received by the slot, the slot and the forward tapered end being positioned radially outward from the middle rib.

9 . The vane of claim 8 , wherein a seal is formed between the forward tapered end and the forward baffle that remains sealed in response to at least one of the forward baffle or the aft baffle moving forward or aft.

10 . The vane of claim 1 , wherein at least one of the radially outward curve or the radially inward curve has a radius of curvature between 0.25 inches and 0.35 inches.

11 . A system for reducing pressure loss in a serpentine turn of a vane of a gas turbine engine, the system comprising:
a forward baffle configured to be received by a forward passage of the vane that is separated from an aft passage of the vane by a middle rib, the middle rib being separated from an inner surface of the vane by a gap, the forward baffle having a first circumferential side and a second circumferential side and a slot therebetween on an aft end of the forward baffle, the slot being positioned radially outward from the middle rib; and an aft baffle configured to be received by the aft passage of the vane and having a forward tapered end radially outward from the middle rib and configured to be received by the slot.

12 . The system of claim 11 , further comprising the vane having the forward passage and the aft passage, wherein the forward baffle is received by the forward passage and the aft baffle is received by the aft passage, and wherein a seal is formed radially outward from the middle rib by the forward tapered end being received by the slot.

13 . The system of claim 12 , wherein the seal remains intact in response to at least one of the forward baffle or the aft baffle moving forward or aft.

14 . The system of claim 12 , further comprising a forward rib positioned axially forward of the middle rib and an aft rib positioned axially aft of the middle rib, wherein the inner surface extends axially from the forward rib to the aft rib and has a radially outward curve from the forward rib to the middle rib and having a radially inward curve from the middle rib to the forward rib.

15 . The system of claim 14 , wherein at least one of the radially outward curve or the radially inward curve has a radius of curvature between 0.25 inches and 0.35 inches.

16 . The system of claim 14 , wherein the radially outward curve and the radially inward curve are positioned at an outer diameter edge of the vane.

17 . The system of claim 12 , further comprising a collar extending radially outward from the inner surface, wherein in response to the forward passage receiving the forward baffle, the collar is positioned adjacent the forward baffle on either circumferential side of the forward baffle and configured to be coupled to the forward baffle.

18 . A turbine section of a gas turbine engine comprising:
a rotor configured to rotate in response to a flow of air; and a vane having:
a forward rib and an aft rib positioned axially aft of the forward rib,
a middle rib positioned axially between the forward rib and the aft rib, such that the forward rib and the middle rib define a forward passage and the middle rib and the aft rib defining an aft passage,
a forward baffle positioned in the forward passage and having a first circumferential side and a second circumferential side and a slot therebetween on an aft end of the forward baffle, the slot being positioned radially outward from the middle rib,
an aft baffle having a forward tapered end radially outward from the middle rib and configured to be received by the slot, forming a seal such that air cannot flow through the aft baffle and the forward baffle, and
an inner surface extending axially from the forward rib to the aft rib, being radially separated from the middle rib via a gap such that air can flow between the aft passage and the forward passage via the gap, and having a radially outward curve from the forward rib to the middle rib and having a radially inward curve from the middle rib to the aft rib.

19 . The turbine section of claim 18 , wherein the inner surface is straight at a first location radially outward from the forward baffle and is straight at a second location radially outward from the aft baffle when the forward passage receives the forward baffle and the aft passage receives the aft baffle.

20 . The turbine section of claim 18 , wherein the seal remains intact in response to at least one of the forward baffle or the aft baffle moving forward or aft.

Assignees

• United Technologies Corp

Inventors

• Spangler Brandon W

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F01D5/188

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2230/232

  by welding · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title