Assembly comprising an exhaust case and a downstream rotationally symmetrical part

Abstract

The invention relates to an assembly comprising: a turbomachine exhaust case (110) that includes an external sleeve and an internal sleeve inside the former, both sleeves extending concentrically about a turbomachine axis, and also includes a plurality of arms extending radially between the sleeves; and an annular part (130) that is centered about the axis, is mounted on one sleeve of the exhaust case, and is located downstream of the exhaust case in the direction in which the air flows inside the turbomachine; the assembly is characterized in that the annular part and the sleeve of the exhaust case on which the annular part is mounted each have a circumferential thread (131, 115), said threads cooperating with each other in order to allow the annular part to be screwed onto the sleeve of the exhaust case.

Claims

1. An assembly of a turbomachine comprising: an exhaust case comprising: an outer shroud; an inner shroud concentric with the outer shroud and extending inside the outer shroud, a first circumferential thread being formed in one of the inner shroud and the outer shroud; and a plurality of arms extending radially between the inner shroud and the outer shroud; an annular part, a second circumferential thread being formed in the annular part, the second circumferential thread cooperating with the first circumferential thread to allow mounting by screwing of the annular part on the one of the inner shroud and the outer shroud wherein the first circumferential thread is formed, downstream of the exhaust case with respect to an air flow in the turbomachine; and a stopping system comprising: a groove arranged adjacent to the first circumferential thread and having a bottom; a plurality of threaded openings extending through the annular part and suitable for being located facing the groove when the annular part is screwed on the exhaust case; and a plurality of screws, each screw of the plurality of screws having the end, the plurality of screws being suitable for being screwed into the plurality of threaded openings so that the end of each screw of the plurality of screws comes into abutment against the bottom of the groove in order for the annular part to be stopped in axial translation relative to the exhaust case.

2. The assembly of claim 1, wherein the first circumferential thread formed on a radially outer surface of the one of the inner shroud and the outer shroud.

3. The assembly of claim 1, wherein the groove is circumferential.

4. The assembly of claim 1, wherein the annular part is a mixer or an exhaust nozzle mounted on the outer shroud.

5. The assembly of claim 1, wherein the annular part is an exhaust cone mounted on the inner shroud.

6. The assembly of claim 1, wherein the annular part is an exhaust cone mounted on the inner shroud; wherein each screw of the plurality of screws is further formed to be able to be integrally contained in a volume consisting of an opening of the plurality of the threaded openings and the groove.

7. A turbomachine, comprising an assembly of claim 1.

8. The assembly of claim 1, wherein the first circumferential thread is formed on a radially outer surface of the one of the inner shroud and the outer shroud, in proximity to a downstream edge of the radially outer surface.

9. The assembly of claim 1, wherein the first circumferential thread extends over two to ten turns of the one of the inner shroud and the outer shroud.

10. The assembly of claim 1, wherein a third circumferential thread is formed in the other of the inner shroud and the outer shroud to screw a mixer or an exhaust nozzle on the outer shroud and an exhaust cone on the inner shroud.

11. The assembly of claim 1, wherein the second circumferential thread is formed on a radially inner surface of the annular part.

12. The assembly of claim 1, wherein the first circumferential thread and the second circumferential thread are made by milling.

13. The assembly of claim 1, wherein the groove comprises a plurality of circular sector sections.

Description

DESCRIPTION OF THE FIGURES

(1) Others features, aims and advantages of the invention will be revealed by the description that follows, which is purely illustrative and not limiting, and which must be read with reference to the appended drawings in which:

(2) FIG. 1, already described, shows a turbomachine assembly comprising an exhaust case according to the prior art,

(3) FIGS. 2a and 2b, also already described, are detail views of the assembly of an exhaust case respectively to a mixer and to an exhaust cone according to the prior art.

(4) FIGS. 3a and 3b illustrate an exhaust case according to two variant embodiments of the invention,

(5) FIGS. 4a and 4b illustrate a mixer of an assembly according to an embodiment of the invention,

(6) FIGS. 5a and 5b illustrate an exhaust cone of an assembly according to an embodiment of the invention,

(7) FIG. 6a is a section view of the assembly of an exhaust cone on an exhaust case,

(8) FIG. 6b is a section view of the assembly of a nozzle or a mixer on an exhaust case.

DETAILED DESCRIPTION OF AT LEAST ONE EMBODIMENT OF THE INVENTION

(9) At least one turbomachine assembly 1 will now be described according to one embodiment of the invention.

(10) The assembly 1 comprises an exhaust case 110, the exhaust case being a rotationally part around an axis X-X of the turbomachine. The assembly 1 further comprises at least one annular part screwed onto the exhaust case on a downstream side of the exhaust case with respect to an air flow in the turbomachine—the part having its axis on the axis X-X when it is mounted on the exhaust case.

(11) The annular part may be either a nozzle or a mixer 120, in the case of a bypass type turbomachine, or an exhaust cone 130.

(12) According to an advantageous variant, the assembly 1 comprises an exhaust case 110, an exhaust cone 130, as well as a nozzle or a mixer 120 screwed onto the case 110.

(13) The different components of the assembly will be described in more detail.

(14) Exhaust Case

(15) The exhaust case 110 comprises an inner shroud 111 and an outer shroud 112, the two shrouds being rotationally cylindrical parts extending one inside the other concentrically around the axis X-X of the turbomachine.

(16) The exhaust case further comprises a plurality of radial arms 113 with respect to the axis X-X of the turbomachine, extending between the inner shroud 111 and the outer shroud 112.

(17) The exhaust case 110 further comprises at least one circumferential thread, 114, 115 arranged respectively in a surface of the inner shroud 111 and/or of the outer shroud 112.

(18) Advantageously, the thread 114, 115 is made on a radially outer surface 111*, 112* of the corresponding shroud, in proximity to the downstream edge of said surface.

(19) Each circumferential thread allows mounting by screwing of a respective annular part. The thread thus extends over a plurality of turns of each shroud, preferably between 2 and 10 turns, for example over 4, 5 or 6 turns.

(20) Thus, with reference to FIG. 3a, the exhaust case 110 comprises, on an outer surface 112* of the outer shroud 112, a circumferential thread 114, this thread allowing mounting by screwing of an exhaust nozzle or of a mixer 120 on the outer shroud 112 of the exhaust case 110.

(21) With reference to FIG. 3b, the exhaust case comprises, on the outer surface 111* of the inner shroud 111, a circumferential thread 115, this thread allowing mounting by screwing of an exhaust cone 130 on the inner shroud 111 of the exhaust case 110.

(22) Advantageously, the exhaust case 110 comprises two threads 114, 115 made on the outer 112 and inner 111 shrouds, so as to be able to screw a mixer or an exhaust nozzle on the outer shroud and an exhaust cone on the inner shroud. In this case, the exhaust cone extends inside the exhaust nozzle or the mixer 120, coaxially.

(23) If the exhaust case 110 includes a thread on an inner or outer shroud, the scalloped flange used before for the mounting of the corresponding downstream part by bolting is eliminated.

(24) Exhaust Case or Mixer

(25) With reference to FIGS. 4a and 4b, the annular part able to be screwed onto the exhaust case may be a mixer 120 or an exhaust nozzle.

(26) To allow screwing of the nozzle onto the outer shroud 112 of the case, the latter also comprises a circumferential thread 121. The thread 121 is suitable for cooperating with the thread 114 of the outer shroud 112 of the exhaust case 110. In this regard, the circumferential thread of the mixer or of the nozzle 120 is preferably made on a radially inner surface 122 of it, to cooperate with a thread 114 arranged on a radially inner surface 112* of the shroud 112.

(27) Exhaust Cone

(28) With reference to FIGS. 5a and 5b, the annular part able to be screwed onto the exhaust case may be an exhaust cone 130.

(29) To allow the screwing of the exhaust cone 130 onto the inner shroud 111 of the exhaust case, the latter also includes a circumferential thread 131. The thread 131 is suitable for cooperating with the thread 115 of the inner shroud of the exhaust case 110. In this regard, if the thread 115 is made on an outer surface 111* of the shroud of the case, the thread 131 is made on a radially inner surface 132 of the exhaust cone 130.

(30) Preferably, the threads 114, 115 of the exhaust case 110 as well as the thread(s) 121, 131 of the nozzle/of the mixer 120 and/or of the exhaust cone 130 are suitable for allowing good angular indexing of the downstream part 120, 130 with respect to the exhaust case 110.

(31) For example, the nozzle, the mixer as well as the exhaust cone may have one or more drainage openings which must be situated in the low position when the part is mounted on the case, i.e. substantially vertically below the axis of the turbomachine (“at 6 o'clock”).

(32) The threads of the exhaust case 110 and of the downstream part to be angularly indexed must therefore be suitable for allowing this positioning, by selecting precisely the angular position of the start of each thread on each part. To accomplish this, each thread is preferably made by milling.

(33) Translation Stopping

(34) Advantageously, the assembly 1 further comprises a stopping system 140 in axial translation of the downstream part on the exhaust case. In the case where the assembly 1 comprises a mixer or an exhaust nozzle 120 and an exhaust cone 130 screwed onto the exhaust case, the stopping system 140 is applicable both to stopping translation of the exhaust cone 130 with respect to the case 110 and of the mixer or the nozzle 120 with respect to the case 110.

(35) The stopping system in axial translation is shown in FIG. 6a, for the case where the downstream part is an exhaust cone 130, and in FIG. 6b, in the case where it is an exhaust nozzle or a mixer 120.

(36) The translation stopping system 140 advantageously comprises a groove 141 made adjacently to the thread 114 or 115 of the exhaust case, i.e. on the outer surface respectively of the outer shroud 112 and/or the inner shroud 111 of the exhaust case.

(37) The groove 141 is preferably circumferential. Alternatively, the groove 141 may comprise a plurality of circular sector sections. According to another alternative, less advantageous however for reasons of manufacturability, the groove 141 may be replaced by local machining, disposed at the exact locations of the screws.

(38) In addition, the translation stopping system 140 comprises at least one through opening 142 made in the circumferential wall of the downstream part having the thread 131, 132. Each through opening 142 is threaded.

(39) Preferably, each downstream part (mixer or nozzle 120 or exhaust cone 130) includes a plurality of through openings 142 disposed regularly on the circumference of the wall having the thread. For example, the downstream part may comprise three through openings 142 distributed at a constant angular interval of 120°.

(40) The locations of the openings 142 are selected so that the openings are located facing the groove 141 of the exhaust case when the annular part is screwed onto the case 110.

(41) Finally, the stopping system 140 in axial translation comprises a plurality of screws 143 suitable for being screwed into the openings 142. Each screw is thus received in an opening 142 until it emerges into the groove 141. The end of the screw housed in the groove comes into abutment against the edges of the groove and prevents axial translation of the downstream part with respect to the exhaust case.

(42) Preferably, as may be seen in FIG. 6a, when the downstream part is an exhaust cone 130, each screw 143 is formed so as to be integrally contained in a volume consisting of an opening 142 of the exhaust cone and the groove 141 of the exhaust case, so as not to protrude with respect to the exhaust cone 130.

(43) Indeed, when the screw is disposed in an opening, the head of the screw is at a radially outer surface of the exhaust cone. Yet, as the air flow in the turbomachine takes place between the exhaust nozzle/the mixer and the exhaust cone, the fact that the head of the screw protrudes with respect to the exhaust cone would have an unfavorable impact on the air flow between the exhaust cone and the mixer or the nozzle.

(44) The screws used may be of the type with a head female imprint, called BTR, or with rounded heads.

(45) The replacement of a bolted connection with a screwed connection allows a reduction in the mass of the assembly. Preferably, to reduce the mass more considerably, both the exhaust cone and the nozzle or the mixer are formed to allow them to be screwed onto the exhaust case.