JPH0711259B2 - Exhaust nozzle hinge - Google Patents

Description

Description: BACKGROUND OF THE INVENTION (Technical field) The present invention relates to a hinge that rotatably connects an upstream wall portion and a downstream wall portion adjacent to each other in an axial direction of a gas turbine engine exhaust nozzle (hereinafter, also referred to as pivotal attachment). In particular, it relates to a nozzle hinge having a novel shape for transferring cooling air from an upstream wall portion to a downstream wall portion.

Prior Art The maneuverability of modern high performance aircraft is significantly enhanced by making the role of the engine exhaust nozzle beyond the normal jet acceleration function. Exhaust nozzles with jet deflection capability allow for faster aircraft maneuvers at lower flight speeds than maneuvers possible with conventional control surfaces. In addition, by incorporating thrust reversal capability in the exhaust nozzle, the aircraft can be decelerated very quickly for maneuvering purposes (maneuvering) and can also be decelerated quickly during landing, landing during short-range activities (operations). The gliding can be shortened.

The exhaust nozzle having such an additional function is called a multifunctional exhaust nozzle. First of all, this kind of exhaust nozzle
Shown at 10 in the figure. Nozzle 10 is side wall 12, upstream convergent (tapered)
A two-dimensional exhaust nozzle having a wall portion composed of downstream divergent (sue broad) flaps 16 and 16a arranged between a flap 14 and a side wall 12. Such a two-dimensional nozzle is suitable for multi-functional use. Unlike axisymmetric nozzles with a circular cross section, the two-dimensional nozzle differentially actuates the flaps 16 and 16a, which allows the flow of hot combustion gases from the nozzles to be deflected, allowing for rapid pitch maneuvering of the aircraft. Because it enables it. The differential operation of such flaps 16 and 16a is shown in FIGS. FIG. 2 shows the positions of the flaps 16 and 16a during normal thrust operation. FIG. 3 shows the deflected positions of flaps 16 and 16a during rapid pitch maneuvering of an aircraft. FIG. 4 shows the flaps 14, 16 and 16a in the closed position, in which the hot combustion gases are discharged through the auxiliary exhaust nozzle 18 to produce reverse thrust.

The wall portion of the exhaust nozzle is exposed to extremely high temperatures from the stream of hot combustion products discharged through the nozzle 10, thus cooling the inner surface of the wall portion to extend the useful life of the nozzle and the need for maintenance. It is preferable to reduce. Typically, a conventional nozzle uses a surface cooling structure for cooling the wall portion of the nozzle as shown in FIG. FIG. 5 diagrammatically shows a portion of the exhaust nozzle 10 including a casing portion 20 located upstream of the converging flap 14 in the hot gas path. Casing 20 includes a liner 22 spaced from its inner surface. Cooling air, which is typically bypass air from a turbine engine, is injected into a cooling air flow passage 24 between casing portion 20 and liner 22. As shown by the broken line arrow in FIG. 5, the cooling air is passed through the cooling air flow passage.
Eject from 24 along the inner surface of flaps 14 and 16 to form a film of cooling air on the inner surface of these flaps.

However, the structure of Figure 5 has significant drawbacks. Primarily,
The cooling air flowing out of the cooling air flow passage 24 is applied to the flaps 14, 16
As they flow along the surfaces of 16a and 16a, they mix with the hot gas in the exhaust gas passage, and the cooling air becomes insufficient.
This lack of cooling air requires an excessive amount of cooling air flow to cool the flaps 14, 16 and 16a. Since the cooling air flow is typically taken from turbine engine bypass air, excess cooling air flow leads to poor performance. Still referring to FIG. 6, when the flaps 14, 16 and 16a are deflected for pitch control of the aircraft, the convergent flap 14 and the divergent flaps 16 and 16a
A severe angle is created at the juncture with the resulting local flow separation 28 downstream of the throat 30. The inner surfaces of flaps 16 and 16a will overheat as long as they rely on a conventional film of cooling air injected upstream of the flaps for cooling. This is because the turbulent flow in the separated flow region 28 mixes the film of cooling air with the hot gas flowing through the exhaust nozzle, thereby severely reducing the effectiveness of this type of cooling structure.

The problem of cooling the nozzle wall is equally applicable to axisymmetric nozzles as well as the multifunctional two-dimensional exhaust nozzle.
The problems associated with cooling the rearmost divergent nozzle flaps of multifunctional two-dimensional exhaust nozzles are exacerbated for two basic reasons. First, the divergent flaps of a two-dimensional nozzle are longer than the axisymmetric nozzle flaps for the same nozzle size and flow area, and are therefore more difficult to cool with the traditional method of injecting a film of cooling air into the flap hinge. is there. The flap of the two-dimensional exhaust nozzle is longer than the flap of the axisymmetric nozzle because the side wall of the two-dimensional nozzle is fixed and therefore all necessary nozzle area changes must be covered by the flap movement. The tip of the two-dimensional nozzle flap moves over a wide stroke to create the required area change and the flap must necessarily be long, so the nozzle flap outer contour angle reduces the drag of the aircraft and thus the performance. Small as needed for.

Secondly, and in connection with the above-mentioned reason, during the operation of the two-dimensional type exhaust nozzle in the state where the jet is fully deflected, a severe angle is formed at the joint between the converging flap and the diverging lap, and FIG. Local flow separation occurs downstream of the throat, as described in connection with.

In fact, the flap of the two-dimensional exhaust nozzle, which is cooled by the film of cooling air injected into the hinge, is generally inefficient because the flow of cooling air injected into this kind of film is not efficient. Exposed. As a result of such low efficiency, some of the exhaust nozzles currently in use suffer from distortion (deformation), thermal fatigue, and cracks on the flap surface. In addition, as the overall engine efficiency is increased in response to the ever existing need to improve aircraft fuel economy and range, bypass air is increasingly being used to cool exhaust nozzle flaps. Controlling the nozzle flaps to the proper temperature in modern engines generally requires more efficient convective cooling means that can distribute the cooling air more evenly across the wall of the nozzle.

Therefore, an object of the present invention is a hinge that rotatably connects the upstream wall portion and the downstream wall portion of the exhaust nozzle, and can efficiently transfer the cooling air from the upstream wall portion of the nozzle to the downstream wall portion. To provide a hinge.

Another object of the present invention is a hinged connection between adjacent upstream and downstream wall portions of an exhaust nozzle, the liner being disposed on the inner surface of the nozzle wall portion to provide a cooling air flow passage therebetween. Providing a hinged connection that can be defined.

Another object of the present invention is a hinge that connects the upstream wall portion and the downstream wall portion of the exhaust nozzle adjacent to each other, and can efficiently transfer cooling air along the inner surfaces of the upstream and downstream wall portions of the nozzle. SUMMARY OF THE INVENTION It is an object of the present invention to provide a hinge that can reduce the amount of cooling air flow required and thus improve the performance and efficiency of an aircraft prime mover.

Other objects and advantages of the invention will be pointed out in the ensuing description, in part will be obvious from the description, and may be realized by practice of the invention. The objects and effects of the present invention can be realized and achieved by the means and combinations described in the claims.

In order to achieve the above-mentioned object, according to the present invention, the first wall portion and the second wall portion of the gas turbine engine exhaust nozzle are connected in the axial direction, and the relative positions of both portions. A hinge is provided to allow pivoting. Each of the first and second wall portions has an inner surface and a liner, the liner being attached to each of the inner surfaces of the wall portion and spaced from the inner surface to provide first and second cooling air flow passages therebetween. To define The hinge comprises a curved portion, leaf seal means, plenum means and offset bracket means. A curved portion having a curved surface is formed at the first end of one of the first and second wall portions. Leaf seal means is secured to and extends from the other first end of the first and second wall portions and extends when the first and second wall portions pivot relative to each other. Slidably abuts the curved portion to form a substantially airtight seal between the leaf seal means and the curved portion. Plenum means is defined at least in part by the leaf seal means and a first end of the other wall portion and is in flow communication with the first and second cooling air flow passages. Offset bracket means rotatably connect the first and second wall portions at their respective first ends.

In a preferred embodiment, the first wall portion is located upstream of the first wall portion in the gas flow path through the exhaust nozzle and a curved surface is formed at the upstream end of the second wall portion. The liner of the second wall portion is formed to include a curved upstream end portion, and the curved upstream end portion is spaced apart from the curved portion of the second wall portion to define a portion of the cooling air flow passage of the second wall portion. To do. In such a structure, the liner of the first wall portion is shaped to include a downstream end portion, the downstream end portion terminating near the curved end portion of the liner of the second wall portion and spaced from the curved end portion, Moreover, it is in a sealing engagement relationship with the curved end portion. According to this structure, when the first and second wall portions pivot relative to each other, the curved upstream end portion of the liner of the second wall portion follows the downstream end portion of the liner of the first wall portion, And remains in sealing engagement therewith, thus maintaining a continuous flow path from the first cooling air flow passage through the plenum means to the second cooling air flow passage without significant leakage therefrom.

Description of Embodiments A presently preferred embodiment of the present invention will be described in detail with reference to the accompanying drawings. Note that, as described above, the present invention is equally applicable to the axially symmetric exhaust nozzle, which is similar to the multifunctional two-dimensional exhaust nozzle. However, for purposes of describing the preferred embodiment of the present invention, the following description will be directed primarily to a hinge incorporating the inventive concept of connecting the first and second wall portions of a two-dimensional exhaust nozzle. However, it is not limited to this. Further, a plurality of hinges of the present invention can be incorporated in a predetermined exhaust nozzle to connect various pivot wall portions,
Since each hinge has substantially the same structure, here 1
Only one hinge will be explained. It will be apparent to those skilled in the art that the description of the hinged connection pivoting the wall portion of the two-dimensional nozzle is equally applicable to the wall portion connection of axisymmetric nozzles and other modified multifunction exhaust nozzles.

According to this invention, the first wall portion and the second wall portion of the exhaust nozzle are provided.
Hinge means are provided for connecting the wall portions. In this embodiment, as shown in FIGS. 7 and 8, the hinge means comprises a hinge, generally designated 100. The hinge 100 connects the first wall portion 102 and the second wall portion 104 and allows relative pivoting between the first wall portion 102 and the second wall portion 104. First wall portion 102
And the second wall portion 104 has inner surfaces 106 and 108, respectively.
Have. Wall portions 102 and 104 further include liners 110 and 112, which are inner surfaces 106.
And 108 to define cooling air flow passages 114 and 116 therebetween.

According to the invention, the hinge comprises a curved portion formed at one of the first ends of the first and second wall portions. In the preferred embodiment of the invention shown in FIGS. 7 and 8, a curved portion 118 is formed at the first end 120 of the second wall portion 104.

According to the invention, the hinge further comprises a substantially airtight seal between the curved portion of the second wall portion and the first end of the first wall portion as the first and second wall portions pivot relative to each other. A sealing means for forming a simple seal. Preferably, the sealing means is secured to and extends from one of the wall portions to slidably abut the other wall portion as the first and second wall portions pivot relative to each other. Includes leaf seal means forming a substantially airtight seal between them. As illustrated in FIG. 7, the leaf seal means is secured to the first end 121 of the first wall portion 102 and has a root portion 124 and a bias means 126 cantilevered from the root portion 124. Including 122. Bias portion 126 includes tip portion 128.
The root portion 124 of the leaf seal 122 is attached to the first end 121 of the first wall portion 102 via the bracket 130.
The root portion 124 is clamped to the bracket 130 by a bolt connection 132. Alternatively, the root portion 124 may be attached to the bracket 130 by welding or other fastening means. Meanwhile, the bracket 130 is bolted to the first wall portion 102.
Secured by 134. Of course, bracket 130
Is not limited to the example in which it is connected to the first wall portion 102 with the bolt 134, but may be welded to the wall portion 102 or attached by other known fastening means. Alternatively, the root portion 124 may be directly fixed to the wall portion 102. In this preferred embodiment, the bracket 130 includes a leaf seal 122, as described below.
It serves to position and support the biased portion 126 of the.

In the structure of leaf seal 122 and bracket 130 as shown in FIGS. 7 and 8, the first and second wall portions 102 are
And 104 pivot relative to each other, the tip 128 of the biasing portion 126 conforms to the curved portion 118 of the second wall portion 104 and slidably abuts the curved portion 118, thereby bending the biasing portion 126 and the curved portion 118. Form an airtight seal with the portion 118.

In accordance with the invention, the hinge further includes plenum means at least partially defined by the leaf seal means and the first end of the one wall portion and in flow communication with the first and second cooling air flow passages. As shown specifically in FIGS. 7 and 8, the plenum means comprises a plenum 136 defined at least in part by the first end 121 of the wall portion 102 and the leaf seal 122. The wall portions 102 and 104 are substantially coextensive with one another along their respective first ends 121 and 120. The liners 110 and 112 also have wall portions 102 and 104.
Has a width that is substantially the same as the width. Plenum 136 is first
And extending over substantially the entire width of the first ends 121 and 120 of the second wall portions 102 and 104 to provide a first cooling air flow passage.
A continuous air flow passage is formed between 114 and the first cooling air flow passage 116 and over substantially the entire width of the wall portions 102 and 104. The air flow path of the cooling air through the cooling air flow passage and the plenum is shown in FIG. Thus
The plenum 136 connects the cooling air flow passages 114 and 116 along substantially the entire width of the wall portions 102 and 104 so that through the plenum 136 and along the wall portions 102 and 104,
A uniform flow of cooling air is obtained that does not mix with the hot exhaust gas flowing through the nozzle.

According to the invention, the hinge further comprises offset bracket means for rotatably connecting (pivoting) the first and second wall portions at their respective first ends. As illustrated in FIGS. 7 and 8, the offset bracket means includes at least two brackets 140. As shown in FIGS. 9 and 11, bracket 140 includes a base portion 142 and an arm portion 144 extending from base portion 142. The base portion 142 is secured to the first end 121 of the first wall portion 102 by welding or other suitable fastening means. The at least two brackets 140 are each spaced apart along the width of the first end 121 of the first wall portion 102. The arm portion 144 of the bracket 140 includes a tip portion 146 with a hole 148. Therefore, the tip portion 146 of each bracket 140 is offset from the first wall portion 102 by the length of the arm portion 144. In this way, the bracket 140 provides a structure for pivotally attaching the first and second wall portions while straddling the curved end portion 118 as described below.

Ribs 150 are secured to the second wall portion 104 near its first end 120, such as by welding. Each pair of ribs 150 are spaced apart to receive the tip portion 146 of the bracket 140 therebetween.
Then, a hole 151 is provided which is aligned with the hole 148 when the tip portion 146 is inserted between the ribs 150. The second wall portion 104 is pivotally attached to the tip portion 146 of the arm portion 144 by a pin 152. The pin 152 penetrates the hole 148 of the bracket 140 and the hole 151 of the rib 150 to connect the wall portions 102 and 104 to each other in an assembled state.

The structure of the offset bracket means is such that it straddles the curved portion 118 of the second wall portion 104, while
Allow 02 and 104 to pivot relative to each other in different angular orientations depending on the operating conditions of the nozzle. In this manner, the curved portion 118 remains spaced from the first end 121 of the first wall portion 102 and partially defines the plenum 136. Further, although FIG. 9 shows two or more brackets 140, all of them have substantially the same structure, and thus only one bracket 140 has been described above. In addition, any number of brackets 140 may be arranged along the first ends of the wall portions 102 and 104 to pivotally mount the wall portions in the assembled condition and securely support the wall portions. The invention is shown in the illustrated and described bracket 14.
Without being limited to a particular construction of 0, one of ordinary skill in the art will recognize numerous other constructions of the offset bracket means within the scope of the present invention.

As shown in FIGS. 7 and 8, the liner 112 of the second wall portion 104 includes a curved upstream end portion 154 that is spaced from the curved portion 118 of the second wall portion 104, An uppermost stream portion of the cooling air flow passage 116 is defined between them. The liner 110 of the first wall portion 102 includes a downstream end portion 156 that terminates near the curved end portion 154 of the liner 112 and is spaced apart from the curved end portion 154 and has an air flow passageway between them. 158 is defined.

An airflow passage 158 between the curved upstream end portion 154 of the liner 112 and the downstream end portion 156 of the liner 110 controls the amount of cooling air leaking from the plenum 136, as indicated by arrow 160.
It can be dimensioned to emit a thin film of cooling air along the 12 surfaces. Alternatively, the hinge 100 may have an airflow passage 158.
Means can be provided to seal the. In particular,
As a sealing means, the leaf spring 162 is fixed to the downstream end portion 156 of the liner 110, and the plate portion 164 of the leaf spring 162 is biased to the curved upstream end portion 154 of the liner 112, thereby causing the air flow gap 158. Seal.

The curved portion 118 of the second wall portion 104 includes two or more notch portions 166 shown in broken lines in FIG. Notch 166
Are spaced from each other along the width of the wall portion 104 and the bracket 140
It corresponds to the arm portion 144 of. As the first and second wall portions 102 and 104 pivot relative to each other about the offset bracket means, the arm portion 144 is curved.
Access to the notch portion 166 of the 18 is possible. Wall part 1
When 02 and 104 are in relative positions such that the exhaust nozzle assumes a full deflection configuration as shown in FIG. 3, the curved upstream end portion 154 of the liner 112 extends upwardly into the plenum 136 and the arm portion 144 extends into the notch portion. Enter 166. This position (8th
In the figure), the flow path of the cooling air through the air flow passage 114 is indicated by the arrow 1
As shown at 38, it enters the plenum 136 and then circulates around the end of the curved upstream end portion 154 and descends into the cooling air flow passage 116.

As shown in FIG. 9, the leaf seal 122 extends along the width of the wall portions 102 and 104 and is divided by brackets 140 that are spaced apart in the width direction of the wall portion 102.
As such, the leaf seal 122 does not interfere with the bracket 140 as the wall portions 102 and 104 pivot relative to each other. To control leakage from the plenum 136 through the notch portion 166, a local edge side 168 is attached to the tip portion 128 of each leaf seal cantilever portion 126 to offset the first and second wall portions 102 and 104. Edge side 168 spans between notch portions 166 to seal plenum 136 as it pivots about the bracket means to progressively larger angles. In this way, the notch portion 166 seals at the edge 168 as the two wall portions pivot relative to each other and the curved end portion 1 of the wall portion 104 for each angular orientation of the wall portions.
Sealing 18 minimizes potential leakage loss of cooling air from the plenum 136. Similarly, downstream end portion 156 of liner 110 and curved upstream end portion 154 of liner 112.
Leakage through the air gap 158 between and can be minimized by providing a leaf spring 162 in this gap 158.

A third point where cooling air may leak from the plenum 136 is at the outermost connection between the wall portions 102 and 104,
These outermost connections are where they abut the adjacent wall portions. To minimize leakage of cooling air from the side ends of the plenum 136, an end cap 170 is attached to the side end of the first end 121 of the wall portion 102, as shown in FIGS. 10 and 11. Seal the plenum 136 at its side edges.
End cap 170 includes leaf seal 122 and bracket 13
It fits snugly at the zero end to minimize cooling air flow loss between the mating surfaces. Cylindrical seals 174 are inserted into each of the outermost portions of the curved portion 118 of the wall portion 104 to control leakage at the interface between the wall portions 102 and 104 and the sidewall 172 of the nozzle. Spring 176 for each cylindrical seal 1
Each cylindrical seal 174 may be inserted into 74 to bias against abutment 177 and pressed against the corresponding nozzle sidewall 172. Again, the wall part 102
Since the end caps 170 and associated cylindrical seals 174 located at the outermost ends of and are only of substantially the same construction, only one end configuration has been shown and described.

In the preferred embodiment of the present invention described above, the second wall portion
104 constitutes the divergent flap of the two-dimensional exhaust nozzle, the first
The wall portion 102 constitutes the convergent flap of the exhaust nozzle. The convergent flap 102 is located upstream of the divergent flap 104 in the exhaust gas flow path through the nozzle. The liners 110 and 112 of the converging flap 102 and the diverging flap 104 define a portion of the gas flow path through the nozzle. However, the invention is not limited to use at the connection between the converging and diverging flaps of a two-dimensional nozzle. As another example, as shown in FIG. 12, the technical idea of the present invention is to apply the hinge connection between the nozzle casing portion and the converging wall portion, for example, the hinge between the nozzle casing portion 202 and the converging wall portion 102. It can be applied to the connecting portion 200. A liner 204 is spaced from the casing portion 202 to define a cooling air flow passage 206 therebetween. In this embodiment, the cooling air flowing through the passageway 206 is coupled to the hinge connection 2
It enters the plenum 208 at the 00 position, enters the cooling air flow passage 114 from the plenum 208 along substantially the entire width of the converging wall portion 102, and then reaches the plenum 136 of the hinge connection 100. Cooling air flows from the plenum 136 into the cooling air flow passage 116 of the diverging wall portion 104. Therefore, the present invention can be applied to each pivot portion of the wall portion that defines the gas passage of the exhaust nozzle.

Further, in the above description, the preferred embodiment of the present invention shows that the curved portion 118 is formed at the first end 120 of the wall portion 104 and the leaf seal means is secured to the first end 121 of the wall portion 102. 12
Described as extending from 1. However, it is also within the scope of this invention that a curved portion is formed at the first end 121 of the wall portion 102 and the leaf seal means and offset bracket means extend from the first end 120 of the wall portion 104. In such an arrangement, the plenum means is also at least partially defined by the leaf seal means and the first end of the one wall portion, and the cooling air flow is cooled from the cooling air flow passage 114 to and from the plenum 136. It is guided to the air flow passage 116.

The present invention is directed to transferring a cooling air flow from an upstream cooling air flow passage defined by a liner spaced from an upstream wall portion to a downstream cooling air flow passage defined by a liner spaced from a downstream wall portion. A novel structure of an exhaust nozzle hinge is provided. This arrangement is particularly suitable for a two-dimensional exhaust nozzle having a relatively long divergent flap length, which allows more efficient utilization of the cooling air passing through the cooling air flow passage. By applying the present invention, thermal deformation and thermal fatigue of the wall portion of the exhaust nozzle can be avoided, and the maintenance management thereof can be generally improved.

Effects and modifications other than those described above will be readily apparent to those skilled in the art. The invention is not broadly limited to the details, representative devices and illustrative examples described and illustrated above. Therefore, various modifications can be made from these details without departing from the scope of the present invention.

[Brief description of drawings]

FIG. 1 is a perspective view of a typical two-dimensional convergent / divergent exhaust nozzle, FIG. 2 is a schematic side view showing the nozzle of FIG. 1 with the nozzle flaps in the full jet thrust position, and FIG. 1 is a schematic side view of the nozzle of FIG. 1 with the nozzle flaps in the aircraft pitch steering position; FIG. 4 shows the nozzle of FIG. 1 with the nozzle flaps in the closed position and exhaust gas through the auxiliary nozzles. FIG. 5 is a schematic side view showing the state of discharge to obtain a reverse thrust suitable for short-range activity, and FIG. FIG. 6 is a schematic diagram showing the flow of film cooling air across the inner surface of the two-dimensional nozzle of FIG. 5, which is the area of flow separation downstream of the hinge connection when the diverging and converging flaps are deflected to the aircraft pitch steering position. FIG. 7 is a side view showing an exhaust nozzle hinge to which the present invention is applied in a state where a wall portion of the nozzle is in a fully closed position for reverse thrust operation, and FIG. 8 is an exhaust nozzle hinge shown in FIG. FIG. 9 is a side view showing the nozzle wall portion in a position in which the exhaust gas flow path is deflected in accordance with aircraft pitch maneuvering; FIG. 9 is a partial perspective view of the exhaust nozzle hinge of FIG. 7;
FIG. 10 shows a bracket pivot connection between the wall parts of the nozzle, FIG. 10 is a partial side view of the exhaust nozzle hinge of FIG. 7, FIG. 11 is a partial plan view of the exhaust nozzle hinge of FIG. 7, and FIG. 1 is a schematic view showing a part of an exhaust nozzle, showing an example in which a hinge according to the present invention is applied to a connecting portion between a convergent flap and a divergent flap and a connecting portion between a convergent flap and a nozzle casing. Description of main symbols 10: nozzle, 12: side wall, 14: converging flap, 16,16a: divergent flap, 100: hinge, 102: first wall portion, 104: second wall portion, 106,108: inner surface, 110, 112: Liner, 114,116: Cooling air passage, 120,121: First end, 122: Leaf seal, 124: Root part, 126: Bias part, 128: Tip part, 130: Bracket, 136: Plenum, 140: Bracket, 142: Base Part, 144: Arm part, 146: Tip part, 148: Hole, 150: Rib, 151: Hole, 152: Pin, 154: Curved upstream end part, 156: Downstream end part, 158: Air flow passage, 162: Plate Spring, 166: Notch part, 168: Addendum, 170: End cap, 172: Nozzle side wall, 174: Cylindrical seal, 176: Spring.

Claims (24)

[Claims] 1. A hinge for axially connecting a first wall portion and a second wall portion of a gas turbine engine exhaust nozzle to permit relative pivotal movement of both portions, said first and second wall portions. Each having an inner surface and a liner, the liner being attached to each of the inner surfaces of the first and second wall portions and spaced from the inner surface to define first and second cooling air flow passages therebetween. In the hinge, the curved portion formed at one of the first ends of the first and second wall portions and the first end of the other of the first and second wall portions are fixed from the first end. An extended leaf seal means,
Leaf seal means for slidably abutting the curved portion to form a substantially airtight seal between the leaf seal means and the curved portion when the first and second wall portions pivot relative to each other; A plenum means at least partially defined by the leaf seal means and a first end of the other wall portion for communicating the first and second cooling air flow passages, and the first and second wall portions. A hinge comprising offset bracket means rotatably coupled at their respective first ends. 2. The first and second wall portions respectively define a convergent flap and a divergent flap for an exhaust nozzle, and a liner spaced from the inner surface of the wall portion defines a portion of a gas flow path through the nozzle. The hinge of claim 1, wherein the converging portion is located upstream of the diverging portion within the gas flow path. 3. The first and second wall portions of the nozzle form a casing portion and a convergent flap of the exhaust nozzle, respectively, and a liner spaced from the inner surface of the wall portion forms a portion of the gas flow path through the nozzle. The hinge of claim 1, which defines and is located in the gas flow path upstream of the converging portion. 4. A liner of the first and second wall portions defines a portion of a gas flow passage through a nozzle, the first wall portion being located in the gas flow passage upstream of the second wall portion. The hinge according to claim 1, wherein the curved portion is formed at an upstream end of the second wall portion. 5. The liner of the second wall portion includes a curved upstream end portion, the curved upstream end portion spaced apart from the curved portion of the second wall portion and defining a portion of a corresponding cooling air flow passage. The hinge according to claim 4. 6. The liner of the first wall portion includes a downstream end portion, the downstream end portion terminating near the curved end portion of the liner of the second wall portion and spaced from the curved end portion therebetween. The hinge of claim 5 defining an air flow passage. 7. The hinge of claim 6 further including means for sealing an air flow passage between a downstream end portion of the liner of the first wall portion and an upstream curved portion of the liner of the second wall portion. . 8. The offset bracket means includes at least two brackets, each bracket secured to a first end of the other wall portion and spaced apart from each other, and a tip extending from the base portion. 2. The hinge according to claim 1, further comprising an arm portion having a wall portion, the one wall portion being rotatably attached to a tip of the arm portion. 9. The sealing means includes at least one leaf seal having a root portion and a bias portion, the root portion secured to the other wall portion and extending between arm portions of the bracket, A biasing portion is cantilevered from a tip of the root portion, the biasing means conforms to the bending portion along at least a portion thereof and the bending portion when the first and second wall portions pivot relative to each other. 9. A shape that slidably abuts against
The hinge described in. 10. The curved portion of the one wall portion includes at least two notch portions spaced from each other to correspond to the arm portions of each of the at least two brackets, the arm portions including the first and second arms. 10. The notch portion can move in and out as wall portions pivot relative to each other about the offset bracket means.
The hinge described in. 11. The leaf seal means includes an edge side portion,
The edge side is attached to the tip of the cantilevered portion of the at least one leaf seal, spans the notch of the curved portion, and the first and second wall portions gradually move around the offset bracket means. 11. The hinge of claim 10 which seals the plenum means when pivoting to a large mutual angle. 12. The width of each of the first and second wall portions along a first end thereof is substantially coextensive with each other, and the plenum means and the liner are first and second wall portions of the first and second wall portions. Extending over substantially the entire width of one end to form a continuous air flow passage along the width between the first and second cooling air flow passages, wherein a hinge further comprises the plenum means at its side end. A hinge as claimed in claim 1 including means for sealing. 13. The first and second wall portions are respectively disposed between and adjacent to the side wall portions of the two-dimensional exhaust nozzle to form a convergent flap portion and a divergent flap portion, the side of the plenum means. An end sealing means is attached to a side end of the other one of the converging and diverging flaps to seal the plenum at its side end, and one of the converging and diverging flaps is curved. 13. The method of claim 12 including a pair of cylindrical seals sized to slidably fit in the outermost portion of the section and spring means for biasing the pair of cylindrical seals toward the sidewall portion of the nozzle. Hinge. 14. A gas turbine engine having a nozzle defining an exhaust gas flow path, comprising a plurality of pairs of upstream and downstream nozzle wall portions, each of the wall portions being substantially coextensive at a first end thereof. Of a plurality of pairs, each wall portion further including a liner, the liner spaced apart from the inner surface of the corresponding wall portion to define a cooling air flow passage therebetween. Hinge means for rotatably connecting the wall portions at their respective first ends, said hinge means comprising a curved portion formed at a first end of one of said pair of said upstream and downstream wall portions; Leaf seal means secured to and extending from the other first end of the pair of upstream and downstream wall portions, wherein the leaf seal means is adapted to engage the curved portion when the upstream and downstream wall portions pivot relative to each other. Sliding freely A leaf seal means forming a substantially airtight seal between the leaf seal means and the curved portion; and at least partially defined by the leaf seal means and a first end of the other wall portion, A gas turbine engine comprising: plenum means for communicating the first and second cooling air flow passages; and offset bracket means for rotatably connecting the upstream and downstream wall portions of each pair at their respective first ends. 15. The liner of one of the upstream and downstream wall portions includes a curved end portion, the curved end portion spaced apart from the curved portion of the one wall portion of a corresponding cooling air flow passage. 15. The engine of claim 14 defining a portion. 16. The liner of the other wall portion of the upstream and downstream wall portions includes an end portion, the end portion terminating near the curved end portion of the liner of the one wall portion and spaced from the curved end portion. To define an airflow passage between them.
Engine described in 15. 17. A means for sealing an air flow passage between a downstream end portion of the liner of the other wall portion of the upstream and downstream wall portions and an upstream curved portion of the liner of the one wall portion. The engine according to claim 16. 18. The offset bracket means includes at least two brackets, each bracket being secured to a first end of the other of the upstream and downstream wall portions and spaced apart from each other; and 15. The engine according to claim 14, further comprising an arm portion extending from a base portion and having a tip, wherein the one wall portion is rotatably attached to a tip of the arm portion. 19. The leaf seal means includes at least one leaf seal having a root portion and a bias portion, the root portion secured to the other wall portion of the upstream and downstream wall portions and the arm portion of the bracket. Extending between the biasing portion is cantilevered from the tip of the root portion, the biasing means conforms to the curved portion along at least a portion thereof and the upstream and downstream wall portions are pivoted relative to each other. 19. The engine according to claim 18, which has a shape that slidably contacts the curved portion when moving. 20. The curved portion of one wall portion of the upstream and downstream wall portions includes at least two notch portions spaced apart from each other to correspond to the arm portions of each of the at least two brackets. 20. The engine of claim 19, wherein said engine is capable of moving in and out of said notch portion as said upstream and downstream wall portions pivot relative to one another about said offset bracket means. 21. The leaf sealing means includes an edge portion,
The edge side is attached to the tip of the cantilevered portion of the at least one leaf seal, spans the notch of the curved portion, and the upstream and downstream wall portions are progressively larger about the offset bracket means. 21. The engine of claim 20 sealing the plenum means when pivoting to a mutual angle. 22. The plenum means and the liner extend across substantially the entire width of the first ends of the upstream and downstream wall portions and are continuous along the width between the first and second cooling air flow passages. 15. The engine of claim 14, wherein the engine includes a means for sealing the plenum means at its side edges, the means forming a smooth air flow passage. 23. The engine according to claim 14, further comprising a supply source of cooling air and means for introducing the cooling air into the cooling air flow passage of the upstream wall portion. 24. A first gas turbine engine exhaust nozzle.
A hinge for axially connecting a wall portion and a second wall portion to allow relative pivoting of both portions, said first and second wall portions each having an inner surface and a liner, said liner comprising: A hinge attached to each of the inner surfaces of the first and second wall portions and spaced apart from the inner surfaces to define first and second cooling air flow passages therebetween, Between the curved portion formed on one of the first ends and the curved portion of the one wall portion and the first end of the other wall portion when the first and second wall portions pivot relative to each other. A plenum that defines a substantially airtight seal in the plenum and is at least partially defined by the seal means and a first end of the other wall portion and in flow communication with the first and second cooling air flow passages. Means and the above first and second And offset bracket means for rotatably connecting the second wall portions at their respective first ends.