JP4432137B2 - Turbine nozzle support device for gas turbine for jet engine - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a turbine nozzle support device for a gas turbine constituting a jet engine such as an aircraft engine.
[0002]
[Prior art]
The jet engine is equipped with a core engine 5 in which a fan 1, a compressor 2, a combustor 3, and a gas turbine 4 are arranged in the axial center O direction in order from the front end side, as schematically shown in FIG. 3. In addition, a cowl 7 is provided around the core engine 5 through a strut 6 so as to bypass the intake air, and air is taken in from the air intake 8 by the rotation of the fan 1 driven by the gas turbine 4. Most of the fuel is ejected from the cowl 7 as propulsive force, and the remaining part is compressed by the compressor 2 driven by the gas turbine 4, and fuel is combusted by the combustor 3 by the compressed air, and the high-speed combustion gas flow The gas turbine 4 is driven.
[0003]
The gas turbine 4 used in the jet engine has a stationary blade 9 and a moving blade 10 in multiple stages in the direction of the axis O, and a combustor that is a front portion of the stationary blade 9 and the moving blade 10 portion. 4, as shown in detail in FIG. 4, multiple nozzle blades 14 are attached at equal intervals in the circumferential direction between the inner band 12 and the outer band 13 that are concentrically arranged (for example, in the circumferential multiple division (for example, , 38 division) structure of the turbine nozzle 11 is arranged.
[0004]
The turbine nozzle 11 of the gas turbine 4 guides the mainstream gas a that is the combustion gas generated by the combustor 3 toward the stationary blade 9 and the moving blade 10, and generates an axial aerodynamic load (moment load). Therefore, the nozzle flange 15 provided on the rear end side of the inner band 12 is attached to the support flange 17 provided on the rotor side (inner diameter side) casing 16 with a stop pin 18. In addition, since it is important to ensure the sealing property between the mainstream gas a and the secondary air b passing outside the combustor 3, the flange 19 provided at the front end of the outer band 13 has a bent seal ring. The outer diameter side of the seal ring 20 is engaged, and the inner diameter side of the seal ring 20 is fitted into a rearward groove 22 provided at the rear end portion of the outer diameter side frame portion 3 b of the combustor 3. The outer diameter side of the seal ring 21 is fitted into an inward groove 23 provided at the front end of the front end of the combustor 3, and the front surface of the seal ring 21 is brought into contact with the rear end of the inner diameter side frame portion 3a of the combustor 3. Furthermore, the rear surface of the nozzle flange 24 provided on the rear end side of the outer band 13 is opposed to the support flange 25 of the stator side (outer diameter side) casing with a tolerance gap S therebetween.
[0005]
The seal rings 20 and 21 are cut at one place in the circumferential direction for the convenience of assembly.
[0006]
[Problems to be solved by the invention]
However, in the case of the turbine nozzle 11, the nozzle flange 15 bulged to the rear end side of the inner band 12 has a cantilever support structure in which the support flange 17 of the rotor side casing 16 is cantilevered. Since excessive stress acts on the nozzle flange 15, the thickness of the nozzle flange 15 is increased so that the whole does not fall forward and backward as indicated by an arrow X. Therefore, it has become a factor that inhibits weight reduction.
[0007]
Further, since there is a temperature difference between the secondary air passing outside the outer diameter side frame portion 3b of the combustor 3 and the secondary air passing inside (inner diameter side) the inner diameter side frame portion 3a, the outer diameter side frame portion 3b. If an extension difference occurs between the inner ring side frame portion 3a and the outer ring 13 front end of the turbine nozzle 11 and the outer end frame portion 3b rear end of the combustor 3, the seal ring 20 is forced. Since a heavy load is applied, the seal ring 20 may be damaged, and the sealing performance of the outlet portion of the combustor 3 cannot be ensured.
[0008]
Further, since the outer diameter side seal ring 20 and the inner diameter side seal ring 21 have a structure with only one cut in the circumferential direction, if the circumferential temperature distribution is not uniform, for example, a partial portion in the circumferential direction If a deformation such as a wave is generated, sealing performance may not be ensured.
[0009]
Therefore, the present invention makes it possible to reduce the weight of the turbine nozzle and to stably seal even if a difference in extension occurs between the inner diameter side frame portion and the outer diameter side frame portion of the combustor. An object of the present invention is to provide a turbine nozzle support device for a gas turbine for a jet engine, which can be performed, and can provide reliable sealing performance even if the temperature distribution in the circumferential direction of the seal ring is not uniform. It is.
[0010]
[Means for Solving the Problems]
In order to solve the above problems, the present invention provides a number of nozzles between an inner band and an outer band that are concentrically arranged so as to guide a combustion gas flow generated by a combustor to a stationary blade and a moving blade portion. A turbine nozzle having a multi-division structure in the circumferential direction to which blades are attached is arranged at the outlet of the combustor, and a rear side base is arranged so that the turbine nozzle can be tilted rearward on the rear end side of the inner band of the turbine nozzle. fitted from the end portion of the inner diameter side nozzle flange which has overhang in the tape over path shaped so that the thickness becomes thinner toward the inner diameter side, in the groove formed by the front and rear two support flanges provided on the rotor casing to be brought by the support flange, the outer diameter was overhang in the range of the groove at the inner diameter side nozzle flange inclined debt can circumferentially divided parts every locking pin attached to the rear end side of the outer band Side The Rufuranji, leaving a tolerance gap so that it can support when the turbine nozzle has been is tilted backward to face the support flange provided on the stator casing, and a groove inwardly in the front end of the inner band, and The outer band is provided with an outward groove in the circumferential direction, and an inner diameter side seal ring and an outer diameter side seal ring are respectively mounted in the inward and outward grooves. Protrusions are provided on the rear edge of the outer groove and spaced apart in the circumferential direction, and the inner diameter side seal ring and the outer diameter side seal are fixed to the support pins that are inserted and fixed to the projecting pieces. The rings are supported so as to be displaceable in the front-rear direction, and the front surfaces of the inner diameter side seal ring and the outer diameter side seal ring are brought into contact with the rear ends of the inner diameter side frame portion and the outer diameter side frame portion of the combustor. And Unishi was constructed.
[0011]
When a large axial aerodynamic load is applied to the turbine nozzle, the turbine nozzle falls at the mounting portion of the inner diameter side nozzle flange, and is received by the two support flanges on the inner and outer diameter sides. At this time, since the inner diameter side seal ring and the outer diameter side seal ring can freely move back and forth, even if there is a difference in extension between the inner diameter side frame portion and the outer diameter side frame portion of the combustor, the combustor outlet portion Sealability is ensured.
[0012]
Also, the more it formed on two support flanges longitudinal provided to overhang allowed by the rotor casing in the tapered rear surface side so that the thickness becomes thinner toward the inner diameter side to be brought tilt the turbine nozzle to the rear and the inner diameter side seal ring that遊装in the groove of the front end of the inner band at the inner diameter side nozzle flange rear end attached at pinning tiltable in circumferential direction of the divided portions each in the range of the groove The outer diameter side seal ring mounted in the groove at the front end portion of the outer band has a multi-part structure composed of a large number of arc-shaped seal plates arranged in the circumferential direction, and is supported at both ends of each seal plate. By adopting a configuration in which the pin is inserted, even when the temperature of the combustor outlet is not uniform in the circumferential direction, the deformation of the seal ring can be made slight.
[0013]
Further, an inner diameter side nozzle flange is formed on the rear end side of the inner band of the turbine nozzle so that the rear surface side is tapered so that the thickness is reduced toward the inner diameter side so that the turbine nozzle can be tilted rearward. The support flange on the rear side of the support flange, which is attached to each circumferentially divided portion with a stop pin so as to be tiltable within the range of the groove formed by the two support flanges on the front and rear sides, is arranged in the circumferential direction of the inner diameter side nozzle flange. By adopting a polygonal configuration in which the corners are positioned at the divided positions, even if the turbine nozzle falls down, the contact between the inner diameter side nozzle flange and the inner diameter side support flange can be maintained and sealed. be able to.
[0014]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, embodiments of the present invention will be described with reference to the drawings.
[0015]
FIGS. 1A, 1B, and 2 show an embodiment of the present invention. Similarly to the case of the gas turbine 4 for a jet engine shown in FIGS. 3 and 4, the outlet portion of the combustor 3 is shown. In the configuration in which the turbine nozzle 11 is disposed on the rear end portion side of the inner band 12 of the turbine nozzle 11, the thickness is made thinner toward the inner diameter side than the nozzle flange 15 shown in FIG. 4. An inner diameter side nozzle flange 26 having a tapered rear surface is overhanged. On the other hand, a groove 29 is formed in the rotor side casing 16 by two front and rear support flanges 27, 28. The inner diameter side nozzle flange 26 is fitted, and the nozzle flange 26 is attached to the support flanges 27 and 28 by the stop pin 18 at each circumferential division, and the nozzle flange is within the range of the groove 29. 26 can be tilted in the front-rear direction, which is the direction of the axis O (see FIG. 3), so that the front-rear tilting of the entire turbine nozzle 11 can be permitted. Even if the turbine nozzle 11 is tilted, the outer peripheral edge of the support flange 28 is always straight on the surface of the nozzle flange 26 so that the corners 28a are positioned in accordance with every other divided position. So that it can be contacted and sealed.
[0016]
In addition, a hole 30 for allowing the retaining pin 18 to pass is formed in each circumferential division of the inner diameter side nozzle flange 26, and the nozzle flange 26 is provided at the end edge of the hole 30 in the front-rear direction. A chamfer 30a is provided so that the tilt can be easily made. Further, every other hole 30 in the circumferential direction is a long hole extending in the circumferential direction so that it can cope with thermal expansion.
[0017]
On the other hand, the outer diameter side nozzle flange 24 projecting from the rear end portion of the outer band 13 of the turbine nozzle 11 is connected to the support flange 25 provided in the stator side casing through a tolerance gap, as shown in FIG. The axial aerodynamic load acting on the turbine nozzle 11 is received by the two support flanges 28 and 25 through the nozzle flanges 26 and 24 at the two inner and outer diameters.
[0018]
Further, an inward groove 23 is provided in the circumferential direction at the front end portion of the inner band 12 of the turbine nozzle 11, an inner diameter side seal ring 31 is mounted in the groove 23, and a rear edge portion of the groove 23 is provided. Further, the projecting pieces 32 are provided at a required interval in the circumferential direction, and the support pins 33 inserted and fixed to the projecting pieces 32 are inserted into the inner diameter side seal ring 31 so that the inner diameter of the support pins 33 is increased. The side seal ring 31 is supported so as to be displaceable in the front-rear direction, and the front surface of the inner diameter side seal ring 31 is brought into contact with the rear end of the inner diameter side frame portion 3 a of the combustor 3.
[0019]
Furthermore, an outward groove 34 is provided in the circumferential direction at the front end portion of the outer band 13 of the turbine nozzle 11, an outer diameter side seal ring 35 is mounted in the groove 34, and the rear edge of the groove 35 is provided. Protrusions 36 are provided in the peripheral portion at a required interval in the circumferential direction, and support pins 37 that are inserted and fixed to the respective protrusions 36 are inserted into the outer diameter side seal ring 35, and the support pins 37 The outer diameter side seal ring 35 is supported so as to be displaceable in the front-rear direction, and the front surface of the outer diameter side seal ring 35 is brought into contact with the rear end of the outer diameter side frame portion 3 b of the combustor 3.
[0020]
The inner diameter side seal ring 31 includes a large number (for example, 19 pieces) of arc-shaped seal plates 31a arranged in the circumferential direction, while the outer diameter side seal ring 35 also includes a large number (for example, a number of circular seal plates 31 arranged in the circumferential direction, for example, 19) arc-shaped seal plates 35a, and support pins 33 and 37 are inserted into both ends of the seal plates 31a and 35a.
[0021]
When the jet engine is operated, the pressure of the secondary air b passing outside the turbine nozzle 11 is higher than the pressure of the mainstream gas a generated in the combustor 3 and passing through the turbine nozzle 11. As shown in (b), the inner diameter side seal ring 31 and the outer diameter side seal ring 35 of the turbine nozzle 11 receive a large pressure from the rear surface side, and the rear end of the inner diameter side frame portion 3a of the combustor 3 respectively. By pressing against the rear end of the outer diameter side frame portion 3b, the sealing performance of the outlet portion of the combustor 3 is maintained.
[0022]
In the above state, when the turbine nozzle 11 receives a large axial aerodynamic load, stress concentrates on the inner diameter side nozzle flange 26 attached to the support flanges 27 and 28 of the rotor side casing 16. 26 is tapered so that its thickness decreases toward the inner diameter side , so that it is tilted backward at the portions of the support flanges 27 and 28, as shown by a two-dot chain line in FIG. The turbine nozzle 11 is in a state of falling backward as a whole. At this time, since the outer diameter side nozzle flange 24 is brought into contact with the support flange 25 of the stator side casing, the axial aerodynamic load applied to the turbine nozzle 11 is stably at two locations of the support flanges 27 and 28 and the support flange 25. It will be received. Therefore, the weight of the turbine nozzle 11 can be reduced compared to the case of cantilever support as shown in FIG.
[0023]
Further, as described above, even if the turbine nozzle 11 falls down, the inner diameter side seal ring 31 and the outer diameter side seal ring 35 are supported so as to freely move back and forth with respect to the support pin 33 and the support pin 37. Therefore, the state in contact with the rear end of the inner diameter side frame portion 3a and the outer diameter side frame portion 3b of the combustor 3 can be maintained, and the inner diameter side frame portion 3a and the outer diameter side frame portion can be maintained. Even if a difference in thermal elongation occurs in 3b, the contact state can be maintained in the same manner. Therefore, the sealing performance of the outlet part of the combustor 3 can be ensured. Further, at this time, the support flange 28 which is the mounting portion of the inner diameter side nozzle flange 26 has a polygonal shape in which the corner portions 28a are positioned at every other divided position of the nozzle flange 26. Even if it falls down, it is possible to maintain the state in which the outer peripheral edge of the support flange 28 is brought into linear contact with the surface of the nozzle flange 26 without any gap, so that the sealability of this portion can be ensured.
[0024]
Further, the inner diameter side seal ring 31 has a circumferential multi-partition structure by an arc-shaped seal plate 31a, and the outer diameter side seal ring 35 has a similar circumferential multi-partition structure by an arc-shaped seal plate 35a. Therefore, even when the temperature distribution at the outlet portion of the combustor 3 is not uniform in the circumferential direction, the thermal deformation becomes slight, so that deterioration of the sealing performance can be prevented.
[0025]
In the above-described embodiment, the case where the number of divisions of the seal rings 31 and 35 and the number of corners of the support flange 28 are selected according to the two divisions of the turbine nozzle is shown. Of course, any number may be used, and various changes may be made without departing from the scope of the present invention.
[0026]
【The invention's effect】
As described above, according to the turbine nozzle support device for a gas turbine for a jet engine of the present invention, the inner band disposed concentrically so as to guide the combustion gas flow generated by the combustor to the stationary blade and the moving blade portion. A turbine nozzle having a multi-division structure in the circumferential direction in which a large number of nozzle blades are attached between the outer band and the outer band is disposed at the outlet of the combustor, and the turbine nozzle is disposed on the rear end side of the inner band of the turbine nozzle. from the proximal end of the rear side so as to be is tilted rearward inner diameter side nozzle flange which has overhang in the tape over path shaped so that the thickness becomes thinner toward the inner diameter side, two longitudinal provided on the rotor casing the fitting is allowed by the support flange in the groove formed by the support flange, attached at the inner diameter side nozzle flange inclined debt can circumferentially divided parts each the stop pin in the range of the groove The outer diameter side nozzle flange was overhang at the rear end side of the outer band, facing the support flange in which the turbine nozzle is provided on the stator casing leaving a tolerance gap so that it can support when brought into inclined rearwardly Inward grooves are provided in the front end portion of the inner band, and outward grooves are provided in the front end portion of the outer band in the circumferential direction, and an inner diameter side seal ring is provided in the inward and outward grooves. And the outer diameter side seal ring, respectively, and further, projecting pieces are provided on the rear edge portions of the inward and outward grooves at predetermined intervals in the circumferential direction, and are inserted into the respective projecting pieces. The inner diameter side seal ring and the outer diameter side seal ring are supported by a support pin fixed in a displaceable manner in the front-rear direction, and the front surfaces of the inner diameter side seal ring and the outer diameter side seal ring are connected to the combustor. Since it is configured to be brought into contact with the rear ends of the diameter side frame portion and the outer diameter side frame portion, the axial aerodynamic load applied to the turbine nozzle is set to 2 on the inner and outer diameter sides by utilizing the tilt of the turbine nozzle. Since it can be supported by the support flange at the location, the weight can be reduced as compared to the conventional cantilever support, and the turbine nozzle falls down, so that the inner diameter side frame portion of the combustor Even if a difference occurs in the outer diameter side frame part, the sealability of the combustor outlet part can be secured, and the thickness is reduced toward the inner diameter side so that the turbine nozzle can be tilted backward. the rear side by overhang in the tapered attached at the locking pin for each divided portion of the tiltable circumferential direction within the range of the groove to be more formed on two support flanges longitudinal provided on the rotor casing The inner diameter side seal ring mounted in the groove of the front end portion of the inner band and the outer diameter side seal ring mounted in the groove of the front end portion of the outer band, respectively, By adopting a multi-divided structure composed of a large number of arc-shaped seal plates arranged in the circumferential direction and having support pins inserted into both ends of each seal plate, the temperature of the combustor outlet is increased. Even if it is not uniform in the circumferential direction, it is possible to prevent deterioration of the sealing performance, and further, the thickness toward the inner diameter side so that the turbine nozzle can be tilted rearward on the rear end side of the inner band of the turbine nozzle. at thinner as the rear side tapers to flared allowed inside diameter side nozzle flange front and rear two possible tilting range of the groove formed by the support flanges circumferential direction of the divided portions every stop pin Ri support flange on the rear side of the attaching and has the support flange, by the structure where the corners in the circumferential direction of the divided position of the inner diameter side nozzle flange has a polygonal shape so as to position, even fall down turbine nozzle The support flange can be always brought into line contact with the inner diameter side nozzle flange surface without any gap, and an excellent effect can be exhibited.
[Brief description of the drawings]
BRIEF DESCRIPTION OF DRAWINGS FIG. 1 shows an embodiment of a turbine nozzle support device for a gas turbine for a jet engine according to the present invention, in which (A) is a cut side view and (B) is an enlarged view of part A of (A).
FIG. 2 is a BB direction arrow view of FIG.
FIG. 3 is a schematic view showing an example of a jet engine.
4 is an enlarged view of a portion C in FIG. 3;
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 3 Combustor 3a Inner diameter side frame part 3b Outer diameter side frame part 9 Stator blade 10 Moving blade 11 Turbine nozzle 12 Inner band 13 Outer band 14 Nozzle blade 16 Rotor side casing 18 Stop pin 23 Groove 24 Outer diameter side nozzle flange 25 Support flange 26 inner diameter nozzle flange
27 support flange 28 support flange 28a corner 29 groove 31 inner diameter side seal ring 31a seal plate 32 projecting piece 33 support pin 34 groove 35 outer diameter side seal ring 35a seal plate 36 projecting piece 37 support pin

Claims (3)

A turbine having a circumferential multi-partition structure in which a large number of nozzle blades are attached between inner and outer bands arranged concentrically so as to guide the combustion gas flow generated in the combustor to the stationary blade and the moving blade portion. The nozzle is disposed at the outlet of the combustor, and the thickness is reduced from the proximal end on the rear side toward the inner diameter side so that the turbine nozzle can be tilted backward to the rear end of the inner band of the turbine nozzle. the inner diameter side nozzle flange which has overhang in the tape over path shape as, and is fitted in the groove formed by the front and rear two support flanges provided on the rotor casing to the support flange, the range of the groove mounting at the inner diameter side nozzle flange inclined debt can circumferentially divided parts every stop pin, the outer diameter side nozzle flange was overhang the rear end of the outer band, said turbine nozzle Write spaced tolerance gap to be supported when brought into tilted to face the support flange provided on the stator casing, and a groove inwardly in the front end of the inner band and also the front end of the outer band An outward groove is provided in each circumferential direction, and an inner diameter side seal ring and an outer diameter side seal ring are respectively mounted in the inward and outward grooves, and further, after the inward and outward grooves, Protrusions are provided on the edges at predetermined intervals in the circumferential direction, and the inner diameter side seal ring and the outer diameter side seal ring are displaced in the front-rear direction on support pins that are inserted and fixed to the respective protrusions. And a structure in which the front surfaces of the inner diameter side seal ring and the outer diameter side seal ring are brought into contact with the rear ends of the inner diameter side frame portion and the outer diameter side frame portion of the combustor. The Turbine nozzle support apparatus for a gas turbine jet engine. The turbine nozzle by overhang in the tapered rear surface side so that the thickness becomes thinner toward the inside diameter side to be is inclined rearwardly of the groove to be more formed on two support flanges longitudinal provided on the rotor casing Inner diameter side seal ring and outer band mounted in the groove of the front end portion of the inner band on the rear end side of the inner diameter side nozzle flange, which is attached with a stop pin for each circumferentially divided portion that can be tilted within the range The outer-diameter side seal ring mounted in the groove at the front end of each of the plurality of arc-shaped seal plates arranged in the circumferential direction has a multi-divided structure, and support pins are provided at both ends of each seal plate. The turbine nozzle support device for a gas turbine for a jet engine according to claim 1, wherein the turbine nozzle support device is inserted. The inner diameter side nozzle flange rear surface side was overhang and tapered so that the thickness becomes thinner toward the turbine nozzle toward the rear end portion of the inner band of the turbine nozzle to the inside diameter side is caused to tilt rearwardly before and after 2 tiltably supporting flange of the rear side of the support flange is mounted at the circumferential direction of the divided portions every locking pin, divided in the circumferential direction of the inner diameter side nozzle flange in the range of the groove formed by the sheet of the support flange The turbine nozzle support device for a gas turbine for a jet engine according to claim 1 or 2, wherein the turbine nozzle support device has a polygonal shape such that a corner portion is located at a position.

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