JPH076407B2 - Turbo shaft engine - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION The present invention relates to a turboshaft engine having a stator with means for preventing gas from flowing longitudinally or axially around the guide vane stages of the stator.

[0002]

BACKGROUND OF THE INVENTION Many turboshaft engine stators include a double casing formed by an outer casing and a ring. The ring is surrounded by a casing and is composed of a plurality of interconnected elements to which the vanes of the guide stages are fixed. The ring element is screwed to the casing and comprises radial ribs extending in the radial direction, which ribs and the casing are arranged so as to maintain the spacing between the ring and the casing. Engaged. However, due to their good thermal conductivity, these ribs cause a substantial outward heat loss, so that they come into contact with the casing at circumferentially spaced positions. The ribs are provided with openings so that they only do so. The drawback of this configuration is
The volume between the ring and the outer casing is continuous, so that in order to independently change the thermal expansion of each ring element, heating or heating to different parts of the volume between the casing and the ring is performed. By blowing the cooling gas at different temperatures or at different rates, it is not possible to make fine adjustments of the clearance between the rotor blades and each of the ring elements. I can only set the whole thing, but so far I haven't been able to achieve the same accuracy in terms of reducing the gap to a minimum either,
Therefore, the output of the engine is affected.

Therefore, it is desirable to reset the seal at each rib to prevent gas from flowing axially between the casing and the ring element through the openings in the ribs. Some solutions are French Patent No. 246
No. 8738, No. 2482661, and No. 25752
No. 21, as well as U.S. Pat. No. 4,314,793, but is generally rather complex. The object of the present invention is to provide a particularly simple solution to this problem.

[0004]

SUMMARY OF THE INVENTION A turboshaft engine provided by the present invention includes a casing, a plurality of ring elements surrounded by the casing, a guide vane stage secured to the ring element, and a ring element secured to the casing. And a stator having a threaded member. The ring element comprises ribs extending outwardly from the ring element and in contact with the casing so as to separate the ring element from the casing, each of the ribs only having a circumferentially spaced portion of the rib. An opening for bringing the casing into contact, a substantially radial bearing surface arranged inside the opening, and an axial flow of gas between the ring element and the casing through the opening of the rib. And an annular sealing element for preventing Each of the sealing elements comprises a circular base plate (sole plate) and a web extending substantially radially inwardly from the base plate for frictionally engaging the bearing surface of each rib. There is. The web covers the openings in each rib. The casing is formed in a plurality of steps, one for each of the sealing elements, each step having a first compression surface acting radially on the base plate of the respective sealing element, Press the sealing element against each rib,
A second compression surface acting axially on the base plate. The threaded member is inclined with respect to the radial direction such that when the threaded member is tightened, the first and second compression surfaces of the casing steps are simultaneously pressed against the sealing element.

[0005]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT A preferred embodiment of the present invention will now be described with reference to the drawings. The stator of the compressor shown in FIG. 1, which may be formed by a number of interconnected parts, comprises a slightly frustoconical outer casing 1 and a plurality of frustoconical ring elements 2. . The ring elements 2 are connected end-to-end by a mating seam 3 so as to form one continuous ring which is surrounded by the casing 1 and which is substantially parallel to the casing 1. .
Each of the ring elements 2 bears a fixed stator or guide vane 4 stage, the stage of the movable rotor vanes 5 being arranged between successive stages of the fixed vanes 4.

Each of the ring elements 2 is provided with a circumferentially extending rib 6 which projects radially outwards so that its outer edge 7 contacts the casing 1. ing. The rib 6 has a casing 1 and a ring element 2
The volume between and is divided into compartments, and in each compartment,
An opening is provided for the gas supply device for adjusting the clearance between each ring element 2 and the movable vane stage 5 surrounded by each ring element 2. Since these devices do not form part of the invention, only the holes 13 opening through the casing 1 in different compartments are shown.

Each of the ribs 6 is notched over most of its circumference so as to form an opening 14 (best seen in FIG. 3). The opening 14 is the casing 1
Extending over most of the radial height of the ribs 6 up to, so that the ribs are in contact with the casing 1 only through the outer edges 7 of the smaller portion of the ribs between the openings, Thus, the rib 6 allows the casing 1
It significantly limits the heat transferred to. Each of the ribs 6 is provided with a sealing element 8 (described in more detail below), which covers the opening 14 and keeps the compartments separated by the ribs separate from each other. It is working.

Each rib between the openings 14 has an axially projecting flange 9 at its outer edge 7.
The block 10 is provided between the flange 9 and the rib 6 at a position facing the other block 11 formed by making the casing 1 thicker outward.
Are formed. Blocks 10 and 11 are bolts 1
It has aligned holes for receiving 2, which penetrate the blocks 10 and 11. Bolt 12
Serves to firmly connect the casing 1 and the ring element 2.

As can be seen in FIG. 2, each rib 6 is
It has a bearing surface 15 extending in the circumferential direction, which lies in a radial plane and is arranged radially inward of the opening 14. Each of the flanges 9 has another bearing surface 16 lying in the same radial plane, the bearing surfaces 15 and 16 facing towards the associated sealing element 8.

Each of the sealing elements 8 has an outer circular base plate 18 abutting the bearing surface 16 of the flange 9 of the associated rib, and a web 19 extending inwardly from the base plate 18. It is a continuous ring with and. The web 19 has an outer part 21 which is inclined towards the associated rib 6 and a radially inner end 22 which has a bearing surface 23 which abuts the bearing surface 15 of the rib 6. ing. The web 19 is slightly elastic and the inner end 22 extends axially beyond the plane of one end of the base plate 18 when the sealing element 8 is unstressed, as indicated by the dashed line in FIG. It is protruding.

In the region of each rib 6 and associated sealing element 8, the inside of the casing 1 is in steps defining a circular surface 17 which extends axially and a surface 20 which extends radially. Has been formed. The circular surface 17 is the flange 9
And acting radially on the outer surface of the base plate 18,
0 acts axially on the base plate 18 so as to press it against the bearing surface 16 towards the ribs 6.

When the stator is assembled, by tightening the bolts 12 that attach the particular ring element 2 to the casing 1, the step surface 20 acts axially on the base plate 18 so that the surfaces 15 and 23 are separated. The axial displacement of the associated sealing element 8 in the direction of the ribs 6 and the step surface 1 as a result of elastic yielding of the webs 19 when in contact with each other.
Both the radial displacement as a result of the compression exerted by 7 on the base plate 18 in the radial direction occurs. Thus, the sealing element 8 is in firm contact with the faces 15 and 16 of the rib 6 and the faces 17 and 2 of the casing 1 are
It reaches a state where it is in close contact with 0. Faces 15, 16,
The surfaces 17 and 20 and the surface of the sealing element 8 in contact with them are slightly roughened, for example by turning operations, so that no significant flow of gas between the compartments occurs.

The axis X of the bolt 12 can be tilted longitudinally or axially at an angle of about 40 ° or 50 °, depending on whether axial or radial compression is applied. This is a matter peculiar to each embodiment. Of course, other tilt angles can be used. The sealing element 8 fits into the frusto-conical casing 1 before the ring element 2 is mounted in place and bolted.
Since the sealing element 8 can be introduced through the wider mouth, there is no problem.

[Brief description of drawings]

FIG. 1 is a schematic axial cross-sectional view of a part of a turboshaft engine compressor according to the present invention.

FIG. 2 is a diagram for illustrating the configuration according to the present invention in more detail.
FIG.

3 is an axial view of the component shown in FIG.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Casing 2 Ring element 4 Guide vane 6 Rib 8 Sealing element 12 Bolt 14 Opening 15, 16 Bearing surface 17, 20 Compression surface 18 Base plate 21 Web

 ─────────────────────────────────────────────────── ─── Continuation of the front page (71) Applicant 593158858 Societe Nacional de Tude et de Construcion de Mot d'Aviacion, “S.N.U.S.M.A.A.” SOCIETE NATIONAL D'ETUDE ET DE CONSTR UCTION DE MOTEURS D'AVIATION "SNEC M.A." France, Paris, 75015, Boulevard du General Marcial Balun, No. 2 (72) invention Jean-Louis Charbonnel France, Le Mes sur Seine, 77350, Ryu du Parc, No. 32 (72) Inventor Pierre Dubney Saint Souvaire, France Ekor, 77930, Ryu DeTrail, 31st (72) Inventor Christopher Charles Grin United States, Ohio, Hamilton, New London Road, 1230 (72) Inventor Daniel Jean Murray France, Soazi S / Seine, 91450, Alle Goubion St Sill, No. 1 (72) Inventor Jean-Pierre André Joseph Meurin France, Boacette, 77350, Ibis Plas de Verdun (no address) (72 ) Inventor Jackie Serge Naude France, Bonduephle, 91070, Ryu de Perdri, 8th (72) Inventor Gerard Rousborg France, Nadi 77176, Are de Agatos, 60th (72) Inventor Yang・ Joel Marie Rigaud, Pomponne, France, 77400, Ryu de Chenes, No. 8 (72) Inventor Rogi Over Clayton Walker United States, Ohio, Midorutau down, Kirusu-state John Road, No. 7431

Claims (3)

[Claims] 1. A casing, a plurality of ring elements surrounded by the casing, a guide vane stage fixed to the ring element, and a screw thread fixing the ring element to the casing. A stator including a member, the ring element having a rib extending outwardly from the ring element and in contact with the casing so as to separate the ring element from the casing. Each of the ribs has an opening that allows only the circumferentially spaced portions of the rib to contact the casing;
A substantially radial bearing surface provided inside the opening and an annular sealing element for preventing gas from flowing axially between the ring element and the casing through the opening in the rib. Each of the sealing elements extending substantially radially inwardly from the base plate for frictionally engaging a bearing surface of a respective one of the ribs with a circular base plate. A web covering the openings of the respective ribs, the casing being formed by a plurality of steps, one for each of the sealing elements. , Each of said steps having a first compression surface acting radially on said base plate of said respective sealing element and an axial direction on said base plate to press said sealing element against said respective rib. Working A second compression surface defining the threaded member such that when the threaded member is tightened, the first and second compression surfaces of the casing step simultaneously seal the seal. A turboshaft engine that is tilted with respect to the radial direction so that it is pressed against the elements. 2. The turboshaft engine according to claim 1, wherein the inclination of the threaded member is 40 ° to 50 ° with respect to the radial direction. 3. The web of each of the sealing elements has a substantially radial surface that is pressed against the bearing surface of the respective rib, the radial surface of the web comprising: The turboshaft engine according to claim 1, which projects axially beyond a base plate of the sealing element when the sealing element is not stressed.