JP5644302B2 - Axial compressor and gas turbine engine - Google Patents

Description

  The present invention relates to an axial compressor or the like that compresses and conveys a gas such as air in the axial direction.

  An axial flow compressor used in a gas turbine engine such as a jet engine will be briefly described (see Patent Document 1 and Patent Document 2).

  A general axial compressor includes a cylindrical compressor case as a base, and the compressor case extends in the axial direction. In addition, an annular gas passage for circulating (inflowing) gas such as air is formed inside the compressor case.

  In the compressor case, a plurality of stages of compressor stators are provided along the axial direction. The compressor stator at each stage includes a plurality of stationary blades arranged at equal intervals in the circumferential direction, and each stationary blade is located in the gas flow path. In order to achieve stable operation of the axial compressor, each stationary blade (each variable stationary blade) in the compressor stator on the front stage is swingable (rotatable) about the axial center in the radial direction. .

  In the compressor case, a plurality of stages of compressor rotors are provided alternately with the plurality of stages of compressor stators along the axial direction. The compressor rotor at each stage includes a disk provided in the compressor case so as to be rotatable about the axis, and the outer peripheral surface of the disk is a part of the wall surface on the radially inner side of the gas flow path. It constitutes. Further, a plurality of moving blades are arranged at equal intervals on the outer peripheral surface of the disk in the compressor rotor of each stage, and each moving blade is located in the gas flow path.

  Therefore, by rotating the multi-stage compressor rotor, the multi-stage compressor rotor and the multi-stage compressor stator cooperate with each other, and the gas taken into the gas flow path is compressed and conveyed in the axial direction. be able to.

  Here, during low-speed operation of the axial compressor, the flow rate is small and the inlet flow angle of the variable stationary blades is increased, and accordingly, the variable stationary blades are swung in the direction of narrowing (the direction of narrowing the gas flow path). Increase the inlet metal angle of the variable stator vane. On the other hand, at the time of high rotation operation of the axial compressor, the flow rate is large and the inlet flow angle of the variable stationary blades is reduced, and accordingly, each variable stationary blade is swung in the opening direction (the gas flow path opening direction). Reduce the inlet metal angle of the variable vane. As a result, the inlet flow angle of the variable stator vane and the inlet metal can be used during both low and high rotation operation of the axial compressor (from low to high rotation operation of the axial compressor). The incidence, which is the difference from the angle, can be reduced, gas separation can be suppressed, and stable operation of the axial compressor can be achieved.

JP 2002-5096 A JP-A-7-317501 Japanese Patent Laid-Open No. 10-212974

  By the way, as mentioned above, although the incidence can be reduced by increasing the inlet metal angle of the variable stationary blade during low-speed operation, it responds to a request to expand the operating range of the axial compressor to a low flow rate side at a high level. If the variable stator blades are swung greatly in the direction of squeezing, the throat area cannot be secured sufficiently and the gas flow (suction) is hindered, resulting in unstable operation of the axial compressor. become. That is, there is a problem that it is not easy to expand the operating range of the axial flow compressor to a low flow rate side at a high level while achieving stable operation of the axial flow compressor.

  Therefore, an object of the present invention is to provide an axial flow compressor having a novel configuration that can solve the above-described problems.

A first aspect of the present invention, the axial flow compressor for conveying compressed gas into the axial direction, extends to the axial direction, an annular gas passage for circulating gas (inlet) on the inside and formed cylindrical compressor casing, provided along the axial direction in the compressor casing, comprising a plurality of vanes located parallel beauty and the gas flow path at equal intervals in the circumferential direction A plurality of stages of compressor stators and a plurality of stages of compressor stators are alternately provided in the compressor case along the axial direction, and an outer peripheral surface is a part of a radially inner wall surface of the gas flow path. A multi-stage compressor rotor comprising a disk configured and rotatable around an axis, and a plurality of moving blades arranged in the outer circumferential surface of the disk at equal intervals and positioned in the gas flow path Each stator blade in the compressor stator on the front stage side has a diameter A first variable segment blade that is swingable (rotatable) about the axial center of the direction, and the first variable segment blade that is disposed downstream of the first variable segment blade and is about the radial axis. The second variable segment blades are divided into second variable segment blades that are independently swingable (rotatable), and a plurality of the first variable segment blades in the compressor stator on the front stage side are divided into the second variable segment blades. A first swing mechanism that swings independently of the first variable segment blade, and a second swing mechanism that swings the plurality of second variable segment blades in the compressor stator on the front stage independently of the first variable segment blade. Each stator blade in the compressor stator on the front stage side includes a combined state in which the first variable segment blade and the second variable segment blade have a common blade shape, the first variable segment blade, and Second possible It is summarized as a segment wings is switchably configured with separated state exhibiting independent blade shape.

  In addition, in the claims and the specification, “provided” means not only directly provided but also indirectly provided through another member, and similarly , “Arranged” is intended to include being disposed indirectly through another member in addition to being disposed directly. Further, the axial compressor is not limited to that used in a gas turbine engine such as a jet engine.

  Therefore, by rotating the compressor rotors in a plurality of stages, the compressor rotors in a plurality of stages and the compressor stators in a plurality of stages cooperate to compress the gas taken into the gas flow path in the axial direction. Can be transported.

Here, at the time of low rotation operation (at the time of a small flow rate) of the axial flow compressor, each variable stationary blade is switched from the combined state to the separated state. Then, while keeping the variable stator blades in the separated state, the first variable segment blades and the second variable segment blades are swung in the direction in which the first variable segment blades and the second variable segment blades are throttled (in the direction of narrowing the gas flow path). The inlet metal angle of the blade and each second variable segment blade (inlet metal angle of each variable stator blade) is increased. On the other hand, at the time of high rotational operation (at a large flow rate) of the axial flow compressor, each variable stationary blade is switched from the separated state to the combined state. Then, while keeping the variable vanes in the combined state, the first variable segment vanes and the second variable segment vanes are swung in the opening direction (the gas flow path opening direction). Kusuru small inlet metal angle. As a result, the inlet flow angle of the variable stationary blade can be used in both the low-speed operation and the high-speed operation of the axial compressor (from the low-speed operation to the high-speed operation of the axial-flow compressor). And the incidence, which is the difference between the entrance metal angle, can be reduced.

Each variable stator vane is divided into the first variable segment blade and the second variable segment blade disposed on the downstream side of the first variable segment blade, and the first variable segment blade and the second variable segment blade. Since the segment blades are configured to be switchable between the combined state in which a common blade shape is exhibited and the separated state in which the first variable segment blade and the second variable segment blade have independent blade shapes, the shaft during low speed operation of a flow compressor, also be greatly swung to the first variable segment blades and the second variable segment wings diaphragm that direction, it is possible to sufficiently secure the throat area.

  The gist of the second feature of the present invention is that the gas turbine engine includes the axial flow compressor having the first feature.

  According to the feature of the second feature, the same effect as that of the first feature is achieved.

According to the present invention, both the first and second variable segment blades are capable of reducing the incidence and the low-speed operation of the axial compressor during both the low-speed operation and the high-speed operation of the axial-flow compressor. and even significant swung the second variable segment wings diaphragm that direction, it is possible to sufficiently ensure the throat area, while achieving a stable operation of the axial compressor, high an operation range of the axial compressor it can be expanded to the low flow rate side level.

FIG. 1 is a schematic meridional sectional view (side sectional view) showing a main part of an axial compressor according to an embodiment of the present invention, and shows a case during high-speed operation. FIG. 2 is a diagram illustrating the arrow II in FIG. FIG. 3 is a schematic meridional cross-sectional view showing the main part of the axial flow compressor according to the embodiment of the present invention, and shows a case of low-speed operation. FIG. 4 is a diagram showing the arrow IV in FIG. 5 (a) and 5 (b) are schematic partial development views (viewed from the outside in the radial direction) of the compressor stator on the front stage side in the axial compressor according to the embodiment of the present invention. (A) has shown the case at the time of high rotation driving | operation, FIG.5 (b) has shown the case at the time of low rotation driving | operation.

  An embodiment of the present invention will be described with reference to FIGS. 1 to 5A and 5B. In the figure, “F” indicates the forward direction (upstream direction), and “R” indicates the backward direction (downstream direction).

  As shown in FIGS. 1 to 4, an axial compressor 1 according to an embodiment of the present invention is used in a jet engine (an example of a gas turbine engine) and gas (in the embodiment of the present invention, air ) Is compressed in the axial direction (rearward direction) and conveyed. And the specific structure of the axial flow compressor 1 which concerns on embodiment of this invention is as follows.

  The axial flow compressor 1 includes a cylindrical compressor case 3 as a base, and the compressor case 3 extends in the axial direction (front-rear direction). In addition, an annular gas flow path P for allowing gas to flow (inflow) is formed inside the compressor case 3.

  In the compressor case 3, a plurality of stages (only two stages on the front stage are shown in FIG. 1) of compressor stators 5 are provided along the axial direction. Each compressor stator 5 includes an annular band member 7 disposed in the compressor case 3, and an outer peripheral surface of the band member 7 is a flow path surface Pa on the radially inner side of the gas flow path P. It constitutes a part of Further, a plurality of stationary blades 9 are arranged on the outer peripheral surface of the band member 7 so as to be arranged at equal intervals in the circumferential direction, and each stationary blade 9 is located in the gas flow path P.

  In the compressor case 3, a plurality of stages of compressor rotors 11 (only one stage is shown in FIG. 1) are provided alternately with the plurality of stages of compressor stators 5 along the axial direction. The machine rotor 11 is integrally connected to a plurality of turbine rotors (not shown) in a jet engine turbine (not shown). Each compressor rotor 11 is provided with a disk 13 provided in the compressor case 3 so as to be rotatable about an axis, and the outer peripheral surface of the disk 13 is a flow inside the gas flow path P in the radial direction. It constitutes a part of the road surface Pa. Further, a plurality of moving blades 15 are arranged at equal intervals on the outer peripheral surface of the disk 13 in each stage of the compressor rotor 11, and each moving blade 15 is located in the gas flow path P. ing.

  Then, the principal part of the axial flow compressor 1 which concerns on embodiment of this invention is demonstrated.

  Each stator vane (each variable stator vane) 9A in the compressor stator 5 on the front stage side is swingable (rotatable) about a radial axis, and a first variable segment blade 17 and a first variable segment blade 17. The second variable segment blade 19 is arranged on the downstream side (rear side) and swingable (rotatable) around the radial axis. Here, the radially outer spindle (blade shaft) 17e of each first variable segment blade 17 is rotatably supported in the boss hole of the compressor case 3, and the first variable segment blade 17 is radially inner. The spindle (blade shaft) 17 i is rotatably supported in the support hole of the band member 7. Similarly, a radially outer spindle (blade shaft) 19e of each second variable segment blade 19 is rotatably supported by a boss hole of the compressor case 3, and a radially inner side of each second variable segment blade 19 is provided. The spindle 19 i is rotatably supported in the support hole of the band member 7. A double chamfered portion is formed on the radially outer spindle 17 e of each first variable segment blade 17 and the radially outer spindle 19 e of each second variable segment blade 19.

  Outside the compressor case 3, a first swinging mechanism 21 that swings each first variable segment blade (a plurality of first variable segment blades) 17 in each compressor stator 5 on the front stage side is disposed. . Specifically, a first drive ring 23 is disposed on the outer side of the compressor case 3 so as to be movable in the circumferential direction, and the first drive ring 23 is disposed at an appropriate position on the outer side of the compressor case 3. A first actuator 25 (see FIGS. 5A and 5B) such as a first cylinder that moves in the circumferential direction is provided. In addition, one end portion of the first connecting lever 27 is connected to the spindle 17e on the radially outer side of each first variable segment blade 17 through a fixing nut 29 and the like so as not to rotate. The other end is connected to an appropriate position of the first drive ring 23 via a pin 31 or the like so as to be swingable (rotatable).

  Similarly, on the outside of the compressor case 3, a second swing mechanism 33 that swings each second variable segment blade (a plurality of second variable segment blades) 19 in each compressor stator 5 on the front stage side is disposed. Has been. Specifically, the second drive ring 35 is disposed on the outer side of the compressor case 3 so as to be movable in the circumferential direction, and the second drive ring 35 is disposed at an appropriate position on the outer side of the compressor case 3. A second actuator 37 (see FIGS. 5A and 5B) such as a second cylinder that moves in the circumferential direction is provided. Further, one end portion of the second connecting lever 39 is connected to the spindle 19e on the radially outer side of each second variable segment blade 19 through a fixing nut 41 or the like so as not to rotate. The other end is connected to an appropriate position of the second drive ring 35 via a pin 43 or the like so as to be swingable (rotatable).

  Each variable stator vane 9A causes the first variable segment vane 17 and the second variable segment vane 19 to be shared by independently swinging each first variable segment vane 17 and each second variable segment vane 19. Switchable between a combined state (see FIG. 5 (a)) having a blade shape and a separated state (see FIG. 5 (b)) in which the first variable segment blade 17 and the second variable segment blade 19 have independent blade shapes. It is configured.

  Then, the effect | action and effect of embodiment of this invention are demonstrated.

  A turbine is driven by expansion of combustion gas from a combustor (not shown) of a jet engine to rotate a multi-stage turbine rotor, thereby rotating the multi-stage compressor rotor 11 integrally with the multi-stage turbine rotor. Let Thereby, the gas taken in the gas flow path P can be compressed and conveyed in the axial direction by cooperating the multi-stage compressor rotor 11 and the multi-stage compressor stator 5.

When the axial flow compressor 1 is operated at a low speed (at a small flow rate), each variable stationary blade 9A is switched from the combined state to the separated state. A direction in which the first variable segment blades 17 and the second variable segment blades 19 are throttled by the first actuator and the second actuator while the variable stator vanes 9A are kept in the separated state (direction in which the gas flow path P is throttled). To increase the inlet metal angle of each first variable segment blade 17 and each second variable segment blade 19 (inlet metal angle of the variable stator blade 9A). On the other hand, when the axial flow compressor 1 is operated at a high speed (at a large flow rate), each variable stationary blade 9A is switched from the separated state to the combined state. And the direction which opens each 1st variable segment wing | blade 17 and each 2nd variable segment wing | blade 19 by a 1st actuator and a 2nd actuator (direction which opens gas flow path P), keeping each variable stator blade 9A in the said union | combined state is swung to, small inlet metal angle of the variable stator vanes 9A Kusuru. As a result, the inlet flow angle of the variable stator vane 9A in both cases of the low-speed operation and the high-speed operation of the axial compressor 1 (from the low-speed operation to the high-speed operation of the axial compressor 1). And the incidence, which is the difference between the entrance metal angle, can be reduced.

Each variable stator blade 9A is divided into a first variable segment blade 17 and a second variable segment blade 19 disposed downstream of the first variable segment blade 17, and the first variable segment blade 17 and the second variable segment blade 17 are separated. Since the segment blades 19 are configured to be switchable between a combined state in which a common blade shape is exhibited and a separated state in which the first variable segment blade 17 and the second variable segment blade 19 have independent blade shapes, axial flow compression is possible. during low speed operation of the machine 1, also be greatly swung to the first variable segment vanes 17 and the second variable segment wings 19 a diaphragm that direction, it is possible to sufficiently secure the throat area.

Therefore, according to the embodiment of the present invention, in both cases of the low-speed operation and the high-speed operation of the axial flow compressor 1, the incidence is reduced and each time the low-speed operation of the axial flow compressor 1 is performed, also be greatly swung to the first variable segment vanes 17 and the direction that the diaphragm of each second variable segment wings 19, it is possible to sufficiently ensure the throat area, while achieving a stable operation of the axial flow compressor 1, an axial flow compressor the operational range of the machine 1 at a high level can be expanded to the low flow rate side.

  The present invention is not limited to the description of the above-described embodiment, and can be implemented in various modes, such as applying the axial flow compressor 1 used in a gas turbine engine to other axial flow compressors. is there. The scope of rights encompassed by the present invention extends not only to the axial flow compressor 1 but also to a gas turbine engine equipped with the axial flow compressor 1.

P Gas channel Pa Gas channel surface 1 Axial compressor 3 Compressor case 5 Compressor stator 7 Band member 7 Compressor stator 9 Stator blade 9A Variable stator blade 11 Compressor rotor 13 Disc 15 Rotor blade 17 First blade Variable segment blade 17e Radial outer spindle 17i of first variable segment blade Radial inner spindle 19 of first variable segment blade Second variable segment blade 19e Radial outer spindle 19i of second variable segment blade Second variable segment Spindle 21 radially inward of blade 1st swing mechanism 23 first drive ring 25 first actuator 27 first connection lever 33 second swing mechanism 35 second drive ring 37 second actuator 39 second connection lever

Claims (3)

In an axial compressor that compresses and transports gas in the axial direction,
Extends to the axial direction, an annular gas passage is formed tubular compressor case for circulating the gas on the inside,
Provided along the axial direction in the compressor casing, a compressor stator a plurality of stages having a plurality of vanes positioned at equal intervals in the circumferential direction in parallel beauty and the gas flow path,
The compressor case is provided alternately with the compressor stator of a plurality of stages along the axial direction in the compressor case, and the outer peripheral surface constitutes a part of the radially inner wall surface of the gas flow path and rotates around the axis. And a plurality of compressor rotors provided with a plurality of moving blades arranged in the gas flow path so as to be arranged at equal intervals on the outer peripheral surface of the disk,
Each stationary blade in the compressor stator on the front stage side is provided with a first variable segment blade that can swing around a radial axis, a downstream axis of the first variable segment blade, and a radial axis. is divided into a second variable segment wing swingable independently of the first variable segment wings around,
A first swing mechanism that swings the plurality of first variable segment blades in the compressor stator on the front stage side independently of the second variable segment blade;
A second swing mechanism that swings the plurality of second variable segment blades in the compressor stator on the front stage side independently of the first variable segment blade;
The stator blades in the compressor stator on the front stage side are a united state in which the first variable segment blade and the second variable segment blade have a common blade shape, and the first variable segment blade and the second variable segment blade. The axial flow compressor is configured to be switchable to a separated state exhibiting an independent blade shape. The first swing mechanism includes a first drive ring disposed outside the compressor case and movable in the circumferential direction, a first actuator that moves the first drive ring in the circumferential direction, and one end portion of the first drive ring. A first coupling lever coupled to a radially outer spindle of each first variable segment blade in the compressor stator on the front side and having the other end coupled to the first drive ring;
The second swing mechanism includes a second drive ring disposed outside the compressor case and movable in the circumferential direction, a second actuator that moves the second drive ring in the circumferential direction, and one end portion of the second drive ring. The compressor stator on the front side includes a second connecting lever connected to a spindle on the radially outer side of each second variable segment blade and connected to the second drive ring at the other end. The axial flow compressor according to claim 1 . Gas turbine engine characterized by comprising the axial compressor according to claim 1 or claim 2.

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