GAS TURBINE EXHAUST NOZZLE DIVERGENT FLAP SEAL

Abstract

A seal assembly for a nozzle in a gas turbine engine includes a connector having a first hinge portion for attaching to the nozzle, a flat portion for sealing against a wall of the engine; and a first hinge for attaching the connector to the flat portion wherein the connector is adapted to rotate relative to the nozzle and the flat portion is adapted to rotate relative to the connector.

Description

BACKGROUND

The present invention relates to gas turbine engines having convergent/divergent nozzles, and more particularly to a nozzle having an efficient flap seal.

A variable area exhaust nozzle may optimize the thrust produced within a gas turbine engine. In augmented gas turbine engines, variable area, convergent/divergent nozzles provide a multitude of nozzle positions. Exhaust gases exiting the turbines pass through the generally decreasing diameter convergent section before passing through the increasing diameter divergent section.

The convergent section may be pivotally connected to a static outer case and to the divergent section. The divergent section may be pivotally connected to the convergent section and to an actuating system radially outboard of the divergent section. The opposite end of the external bearing is pivotally attached to a static outer case.

The convergent and divergent sections generally include flap seals attached to the convergent or divergent sections or a structural member within the engine. The flap seals accommodate changes in an orifice area by sliding as the orifice area decreases or increases.

SUMMARY

According to an embodiment described herein, a seal assembly for a nozzle in a gas turbine engine includes a connector having a first hinge portion for attaching to the nozzle, a flat portion for sealing against a wall of the engine; and a first hinge for attaching the connector to the flat portion wherein the connector is adapted to rotate relative to the nozzle and the flat portion is adapted to rotate relative to the connector.

According to a further embodiment described herein, a seal assembly for a gas turbine engine includes a connector having a first hinge portion attaching to an engine nozzle, a flat portion sealing against a wall of the gas turbine engine; and a first hinge attaching the connector to the flat portion wherein the connector rotates relative to the nozzle and the flat portion rotates relative to the connector.

According to a still further embodiment described herein, a method of sealing a divergent flap against an edge of an engine wall includes the steps of rotating a connector relative to the divergent flap in response to pressure of gases passing from the engine and rotating a seal relative to the connector in response to the pressure of gases passing from the engine such that the seal seals against the engine wall.

The various features and advantages of the disclosed examples will become apparent to those skilled in the art from the following detailed description. The drawings that accompany the detailed description can be briefly described as follows.

BRIEF DESCRIPTION OF THE DRAWING

FIG. 1A is a general sectional side view of a variable geometry exhaust nozzle as shown in a maximum position, the nozzle being illustrated on one side of its centerline.

FIG. 1B is a general sectional side view of a variable geometry exhaust nozzle shown in a minimum position, the nozzle being illustrated only one side of its centerline.

FIG. 2 shows a perspective view of a prior art divergent flap including a flap seal.

FIG. 2A shows a sectional view taken along the lines 2-2 of the prior art flap seal of FIG. 2.

FIG. 3 shows a schematic view perspective of a flap seal attaching to a divergent flap as disclosed herein.

FIG. 4 shows a schematic view taken along the lines 3-3 of FIG. 3 of the divergent flap of FIG. 3.

FIG. 5 is a cross-sectional, perspective view taken along the lines 5-5 of FIG. 4 shown in a joint between the flap seal and a retention bar for holding flap seal.

DETAILED DESCRIPTION

Referring to FIGS. 1A and 1B, a nozzle system 10 for a gas turbine engine 11 is shown. A nozzle system 10 includes a plurality of distributed convergent flaps 12 (only one shown in section), each pivotally connected to a stationary frame 14 with a cooling liner panel 16 upstream thereof. A plurality of distributed divergent flaps 18 (only one shown in section), are pivotally connected to a joint 20 to an aft section of the convergent flaps 12.

Taken collectively, the convergent and divergent flaps 12, 18 define a nozzle centerline A that defines a boundary of an exhaust gas path. During operation, a control system 21 governs the angular orientation of the convergent flaps 12 and the divergent flaps 18 to adjust a nozzle throat area 34.

FIG. 1A depicts the nozzle 10 in a maximum dilated position, which may be used during use of an afterburner (not shown), and FIG. 1B depicts a nozzle system 10 in a minimally dilated position, which is typically used if the afterburner is not being used.

Referring now to FIG. 2, a prior art flap seal assembly 35 is attached to a divergent flap 18 by a retention bar 40. The retention bar has a rectangular body 45, a plurality of fastener holes 50 which receive fasteners (not shown) to attach the rectangular body 45 to the divergent flap 18.

Referring now to both FIGS. 2 and 2A, the seal 55 is designed to seal against sidewall 60 of the engine to ensure the thrust in exhaust gases F are directed properly through the nozzle assembly 10. Pressure P from the exhaust gases F forces the seal 55 against the sidewall 60 that is flat to provide a seal therebetween. The seal 55 has a flat portion 65 for sealing against the flat sidewall 60 and a bent portion 70 for attaching to the rectangular body 45 as is known in the art. However, the Applicants have discovered that the pressure P also exerts force on the sidewall 60 thereby causing the sidewall 60 to bow. Because the seal 55 hinges about the retention bar 40, if the sidewall 60 bows, it is improbable that the sidewall and the flat portion 65 creates any more than line contact with each other. A line seal may not be sufficient to provide adequate sealing for required performance of the engine 5 (see FIG. 1). The flat portion 65 cannot move in concert with the wall 60 as pressure is applied.

Referring now to FIGS. 3-5, a flap seal assembly 135 is shown. The flap seal assembly 135 includes retention bar 140 having a generally rectangular body 145 having a plurality of fastener holes 150 through which fasteners (not shown) attach the retention bar to the divergent nozzle 18. Seal 155 is attached to a connector 160 via a hinge 165. The connector 160 attaches to the retention bar (or member) 140 as will be discussed infra.

The connector 160 has a plurality of spaced, knurled fingers 170 at first end 175. The knurled fingers 170 grip pin 180 as is known in the art. The connector 160 has a flat body 185 with an indentation 190. The indentation 190 provides axial stiffness of connector 160. At a second end 195, the flat body 185 attaches to the retention bar 140.

Referring now to FIG. 5, the second end 195 has a plurality of notches having an L-shape 200 forming a cutout 202 (see also FIG. 5) and a transverse opening 203 relative to the cutout 202 to create the plurality of fingers 205 in the end portion of the flat body 185.

The retention member or bar 140 has a complex shaped opening 210 for receiving fingers 205. A complex shape of the opening 210 allows the flat body to 185 to rotate relative to the divergent flap 18 and the retention bar 140 without requiring a piano type hinge. A lip 215 extends into the transverse opening 203 of the flat body 185. A generally rectangular space 220 allows fingers 205 to rotate therein. A first chamfered surface 225 angles outwardly away from the divergent flap 18 at an angle to allow the flat body 185 to rotate a particular degree. A second chamfered surface 230 allows the flat body 185 to rotate even further. As the flat body rotates about the chamfered surfaces 225 and 230, the finger 205 moves in the rectangular space 220.

Seal 155 has a hairpin shape. It has a plurality of knurled fingers 235 at a first end 240 thereof for a grasping the pin 180. The knurled fingers 235 cooperate with the knurled fingers 170 of the flat body 185 so that the seal 155 rotates about pin 180 independent of motion of the flat body 185. The seal 155 has a first flat area 245 extending from the knurled fingers 235 to a bend area 250 which bends a bit more than 180° to form the hairpin shape of the seal 155. The bend area 250 attaches to a second flat area 225 which is adapted to contact the sidewall 60 over a large area. A second end portion 260 of the seal 155 attaches to the second flat area 225. The hinge pin 180 is disposed about a midpoint of 265 of the second flat portion 255. The purpose of the hairpin shape is to evenly distribute load between the flat portion 155 and the engine wall 60 by transferring the load induced by the connector 185, around the bend 250.

In operation, pressure P urges the first flat body 185 outwardly away from the divergent flap 18. The pressure P also urges the seal 155 towards the sidewalls. Rotation of the flat body 185 continues until the flat portion 255 is flat against the sidewall 60. If the second end 260 hits the sidewall 60 first, continued rotation of the flat body and rotation of the seal 155 relative to the flat body 185 about hinge pin 180 urges the second flat body 255 against the sidewall. If the sidewall 60 bows due to the pressure P, rotation of the flat body 185 in conjunction with the rotation of the seal 155 relative to the flat body 185 allows the seal 155 to continue to adhere to the sidewall 60 regardless of the bowing, the second flat area 255 continuing to attach along a large area of the sidewall 60.

Although a combination of features is shown in the illustrated examples, not all of them need to be combined to realize the benefits of various embodiments of this disclosure. In other words, a system designed according to an embodiment of this disclosure will not necessarily include all of the features shown in any one of the Figures or all of the portions schematically shown in the Figures. Moreover, selected features of one example embodiment may be combined with selected features of other example embodiments.

The preceding description is exemplary rather than limiting in nature. Variations and modifications to the disclosed examples may become apparent to those skilled in the art that do not necessarily depart from the essence of this disclosure. The scope of legal protection given to this disclosure can only be determined by studying the following claims.

Claims

1. A seal assembly for a nozzle in a gas turbine engine, said assembly comprising: a connector having a first hinge portion for attaching to said nozzle,a flat portion for sealing against a wall of said engine; anda first hinge for attaching said connector to said flat portion wherein said connector is adapted to rotate relative to said nozzle and said flat portion is adapted to rotate relative to said connector.

2. The seal assembly of claim 1 wherein said seal assembly further comprises an attachment member for attaching to said nozzle wherein said attachment member has a second hinge portion wherein said first hinge portion and said second hinge portion cooperate to form a second hinge.

3. The seal assembly of claim 2 wherein said first hinge portion is a finger.

4. The seal assembly of claim 3 wherein said second hinge portion is a hollow area in said attachment member in which said finger is disposed.

5. The seal assembly of claim 4 wherein said hollow area has a first chamfered surface extending therefrom to allow increased rotation of said connector as said finger moves within said hollow area.

6. The seal assembly of claim 5 wherein said hollow area has a second chamfered surface extending from said first chamfered area to allow further increased rotation of said connector as said finger moves within said hollow area.

7. The seal assembly of claim 1 wherein said connector has an indentation therein for providing axial stiffness of said connector.

8. The seal assembly of claim 1 wherein said flat portion has a bent portion for attaching to said first hinge wherein said flat portion and said bent portion form a hair pin shape.

9. The seal assembly of claim 8 wherein said bent portion bends greater than 180°.

10. A seal assembly for a gas turbine engine, said assembly comprising: a connector having a first hinge portion attaching to an engine nozzle,a flat portion sealing against a wall of said gas turbine engine; anda first hinge attaching said connector to said flat portion wherein said connector rotates relative to said nozzle and said flat portion rotates relative to said connector.

11. The seal assembly of claim 10 wherein said seal assembly further comprises an attachment member attaching to said nozzle wherein said attachment member has a second hinge portion wherein said first hinge portion and said second hinge portion cooperate to form a second hinge.

12. The seal assembly of claim 11 wherein said first hinge portion is a finger.

13. The seal assembly of claim 10 wherein said second hinge portion is a hollow area in said attachment member in which said finger is disposed.

14. The seal assembly of claim 13 wherein said hollow area has a first chamfered surface extending therefrom to allow increased rotation of said connector as said finger moves within said hollow area.

15. The seal assembly of claim 14 wherein said hollow area has a second chamfered surface extending from said first chamfered area to allow further increased rotation of said connector as said finger moves within said hollow area.

16. The seal assembly of claim 10 wherein said connector has an indentation therein for providing increased axial stiffness of said connector.

17. The seal assembly of claim 10 wherein said nozzle is a divergent flap.

18. Method of sealing a divergent flap against an engine wall, said method comprising: rotating a connector relative to said divergent flap in response to pressure of gases passing from said engine androtating a seal relative to said connector in response to said pressure of gases passing from said engine such that said seal seals against said engine wall.

19. The method of claim 18 further comprising: providing a finger on said connector andproviding a hollow area in which said finger is disposed and in which said finger moves to allow said connector to rotate relative to said flap.

20. The method of claim 18 further comprising: distributing load evenly between a flat portion of said seal and said engine wall by transferring load induced by the rotating said connector around a bend in said seal.