JP4872006B2 - Gas turbine engine - Google Patents

Description

  The present invention relates to a gas turbine engine including a pipe used for a cooling medium passage, a cable arrangement member, and the like.

  In a gas turbine engine that extracts power with a high-temperature combustion gas obtained by burning air compressed by a compressor, it is necessary to cool the inside of the engine in order to improve engine performance and life. As a structure for cooling the inside of a gas turbine engine, it has been proposed to extend a pipe in the axial direction inside a rotor forming a turbine and use this pipe as a refrigerant passage (for example, Patent Documents). 1).

JP-A-11-257010

  In general, compressor rotors and turbine rotors of gas turbine engines are assembled by connecting a plurality of rotor stages in the axial direction, so pipes are integrally formed in the inner space of the rotor, or fixed like bolts. It is difficult from the viewpoint of productivity to fix the pipe to the rotor using the member. Therefore, it is necessary to insert the pipe into the through hole provided in the rotor before or after the assembly of the rotor. In this case, it is inevitable that a minute gap is generated between the pipe and the peripheral wall of the through hole. As a result, when the rotor rotates at a high speed, the pipe swings around in the through hole, which causes a problem of reducing the efficiency and life of the gas turbine engine.

  In order to solve the above-mentioned problems, the object of the present invention is to prevent the pipes provided in the inner space of the rotor from moving around for the purpose of transferring the cooling medium, arranging the cables, etc., and improving the performance and reliability. The object is to provide an excellent gas turbine engine.

  To achieve the above object, a gas turbine engine according to the present invention comprises a plurality of rotor stages connected in the axial direction, a hollow rotor forming at least one of a compressor and a turbine, A pipe unit inserted in the axial direction in the inner space, and the weight distribution in the cross section of the pipe unit is eccentric with respect to the axis of the rotor.

  According to this configuration, the pipe unit is provided in the inner space of the hollow rotor and is used as a cooling medium passage or a cable arrangement member, thereby suppressing an increase in the overall size of the gas turbine engine, and High performance and high functionality can be achieved. In addition, by decentering the weight distribution of the pipe unit, the pipe unit is displaced only in a specific direction with respect to the rotor when the rotor rotates, so that the swing of the pipe unit in the rotor is suppressed, The reliability of the gas turbine engine is maintained.

  The gas turbine engine which concerns on this invention WHEREIN: It is preferable that the said pipe unit has a tubular member and the flange which is provided in the outer periphery of this tubular member, and fits the inner peripheral surface of the said rotor. In this case, it is further preferable that the weight distribution in the cross section of the flange is eccentric with respect to the axis of the rotor. By providing the flange on the outer periphery of the tubular member, the work of assembling the pipe unit to the rotor and the work of positioning the pipe unit with respect to the rotor are facilitated. Further, by decentering the weight distribution in the cross section of the flange, it becomes easy to manufacture an eccentric pipe unit.

  In the gas turbine engine according to the present invention, the pipe unit forms, for example, a passage of a cooling medium that cools the inside of the gas turbine engine or a passage of seal air that seals a bearing that rotatably supports the rotor. It may be. According to this configuration, the internal space of the rotor can be utilized to cool and seal the inside of the engine, thereby improving performance such as engine efficiency and life while suppressing an increase in the size of the gas turbine engine. To do.

  In the gas turbine engine according to the present invention, when the pipe unit forms a cooling medium passage or a sealing air passage, the rotor is a compressor rotor, and the cooling medium or the sealing air is extracted from the compressor. Compressed air may be used. According to this configuration, cooling or sealing can be efficiently performed using the compressed air of the compressor without separately introducing air for cooling or sealing.

  In the gas turbine engine according to the present invention, a cable may be extended inward of the pipe unit. According to this configuration, as a cable, for example, by extending a wiring for transmitting a measurement signal such as a temperature sensor or a strain sensor in the pipe unit, the inner space of the rotor can be utilized to increase the height of the gas turbine engine. Functionalization can be achieved.

  As described above, according to the gas turbine engine of the present invention, the swing of the pipe attached to the inner peripheral surface of the rotor for the transfer of the cooling medium or the insertion of the cable is prevented, and the performance and reliability of the gas turbine engine are improved. Improves.

1 is a partially cutaway side view showing a gas turbine engine according to a first embodiment of the present invention. It is a longitudinal cross-sectional view which shows the principal part of the gas turbine engine of FIG. It is a figure which shows the example of the pipe unit used for the gas turbine engine of FIG. 1, (a) And (b) is a front view, (c) is a longitudinal cross-sectional view. It is a cross-sectional view which shows the modification of the pipe unit used for the gas turbine engine of FIG. It is a fragmentary sectional view which shows the gas turbine engine which concerns on 2nd Embodiment of this invention. It is a longitudinal cross-sectional view which expands and shows a part of FIG. It is a fragmentary sectional view which shows the gas turbine engine which concerns on 3rd Embodiment of this invention. It is a longitudinal cross-sectional view which expands and shows a part of FIG.

  Embodiments according to the present invention will be described below with reference to the drawings.

  FIG. 1 shows a gas turbine engine (hereinafter simply referred to as a gas turbine) according to a first embodiment of the present invention. In the figure, a gas turbine 1 compresses an externally introduced air IA with a compressor 3 and guides it to a combustor 5 to inject and burn fuel F into the combustor 5 to obtain a high-temperature and high-pressure combustion obtained. The turbine 7 is driven by the gas G. In the following description, the compressor side in the axial direction of the gas turbine 1 may be referred to as “front side” and the turbine side may be referred to as “rear side”.

  In this embodiment, an axial flow type compressor is used as the compressor 3. The axial flow compressor 3 includes a compressor rotor 11 that constitutes a front portion of a rotating portion of the gas turbine 1. The compressor rotor 11 is divided into a front and rear divided type, that is, a compressor rotor main body 11A connected to the front end of the compressor rotor main body 11A and a rear end portion of the compressor rotor main body 11A so as not to be relatively rotatable by a bolt (not shown). It consists of part 11B. A large number of moving blades 13 are arranged on the outer peripheral surface of the compressor rotor main body 11 </ b> A. By combining these moving blades 13 and a large number of stationary blades 17 arranged on the inner peripheral surface of the housing 15, an intake cylinder 19 is provided. The air IA sucked from between the housing 15 and the inner cowl 20 on the inner diameter side thereof is compressed. The compressed air CA is supplied to the combustor 5 through a diffuser 21 disposed on the downstream side of the compressor 3.

  The compressor rotor 11 has a plurality of compressor rotor stages 23 connected in an axially overlapping manner. Each compressor rotor stage 23 has a disk 25 that forms a radially inner portion, and a plurality of rotor blades 13 are implanted on the outer periphery of the disk 25 at equal intervals in the circumferential direction. The compressor rotor 11 is formed in a hollow shape. That is, each compressor rotor stage 23 has a through hole 27 penetrating in the axial direction at the center of the disk 25, and the entire compressor rotor 11 is a hollow portion 29 formed by the through hole 27. have.

  A plurality of the combustors 5 are arranged at equal intervals along the circumferential direction of the gas turbine 1. In the combustor 5, the compressed air CA supplied from the compressor 3 is mixed with the fuel F injected into the combustor 5 and burned, and the high-temperature and high-pressure combustion gas G is converted into a turbine nozzle (first stage stationary blade). 23 flows into the turbine 7.

  The turbine 7 includes a turbine rotor 33 that forms a rear portion of the rotating portion of the gas turbine 1 and a turbine casing 35 that covers the turbine rotor 33. A plurality of stages of turbine stationary blades 37 are attached to the inner peripheral portion of the turbine casing 35 at a predetermined interval. On the other hand, the turbine rotor 33 has a plurality of stages so as to be positioned downstream of the turbine stationary blades 37 of each stage. The turbine rotor blade 39 is provided. The entire two rotors 11 and 33 are rotatably supported by the housing 15 via a front bearing 43, a central bearing 45, and a rear bearing 47.

  A pipe unit 51 is inserted through the hollow portion 29 of the compressor rotor 11 in the direction of the rotor axis C. Specifically, the pipe unit 51 includes a plurality of steel tubular members 53 having an outer diameter smaller than the diameter of the through hole 27, and a plurality of steel flanges 55 provided on the outer periphery of the tubular member 53. And is inserted into the hollow portion 29 of the compressor rotor 11 from the front side. The front end portion 51 a of the pipe unit 51 is fixed to the compressor rotor 11 via a disk-shaped support member 56 positioned at the front end portion 11 a of the compressor rotor 11.

  As shown in FIG. 2, a plurality of tubular members 53 are arranged in series along the rotor axis C, and the adjacent tubular members 53 are connected by a flange 55. More specifically, the flange 55 includes an inner peripheral wall 55a that is fitted to the outer peripheral portion of the opposite end portions of the tubular members 53 and 53, and an outer peripheral wall 55b that is fitted to the inner peripheral surface 11b of the compressor rotor 11. The peripheral wall 55a and 55b are connected to each other, and the two tubular members 53 and 53 are connected to each other by being welded to the inner peripheral wall 53a. A slight gap S for inserting the flange 55 into the through hole 27 exists between the outer peripheral wall 55 b of the flange 55 and the inner peripheral surface 11 b of the compressor rotor 11. As shown in FIG. 1, a plurality of flanges 55 (six in this embodiment) are provided at different positions in the axial direction, but only one flange 55 may be provided.

  As shown in FIG. 3, the pipe unit 51 has a weight distribution (hereinafter simply referred to as “weight distribution”) in a cross section orthogonal to the rotor axis C so as to be eccentric with respect to the rotor axis C. Is formed. As a structure for decentering the weight distribution of the pipe unit 51, it is preferable to decenter the weight distribution of the flange 55 with respect to the rotor axis C.

  Specifically, for example, as shown in the front view of FIG. 3A, the weight distribution can be decentered by embedding a weight 57 in a part of the connection wall 55 c of the flange 55. Alternatively, as shown in the front view of FIG. 3B, a part of the connecting wall 55c of the flange 55 may be cut away to provide an axial through hole 59, which is shown in the longitudinal sectional view of FIG. As shown, a thin portion 61 in which a part of the connecting wall 55c of the flange 55 is thinned may be provided.

  The eccentric amount of the weight distribution of the pipe unit 51 may be small. For example, in the rotation speed region of 60% or more of the rated rotation speed of the compressor rotor 11, the flange 55 is rotated by the rotation of the flange 55 integral with the compressor rotor 11. The outer peripheral wall 55 b may be pressed against the inner peripheral surface 11 b of the compressor rotor 11.

  Thus, the pipe unit 51 is configured such that the flange 55 is provided on the outer periphery of the tubular member 53, so that the work of assembling the pipe unit 51 to the rotor and the work of positioning the pipe unit 51 with respect to the rotor are facilitated. Further, by decentering the weight distribution of the flange 55, the pipe unit 51 having an eccentric weight distribution can be easily manufactured.

  However, the structure of the pipe unit 51 is not limited to the example of FIG. 1 having the tubular member 53 and the flange 55 as long as the pipe unit 51 has a space extending in the axial direction and the weight distribution is eccentric. 4, the flange 55 may be omitted and only the tubular member 53 may be configured. In the case where the pipe unit 51 is composed only of the tubular member 53, for example, as shown in the figure, by setting the thickness of the peripheral wall 53a asymmetric with respect to the rotor axis C, the weight distribution can be decentered. .

  In the present embodiment, as shown in FIG. 1, the pipe unit 51 is formed as a passage (refrigerant passage) RP of the cooling medium RA that cools the inside of the gas turbine 1. The pipe unit 51 extends from the front end portion 11 a to the rear end portion 11 c of the compressor rotor 11. The front end portion 51 a of the pipe unit 51 passes through the support member 56 and communicates with the compressed air extraction passage 63. On the other hand, the rear end portion 51 b of the pipe unit 51 opens toward the turbine rotor 33. Accordingly, the compressed air CA extracted from the compressor 3 through the compressed air extraction passage 63 is guided to the periphery of the turbine rotor 33 through the refrigerant passage RP in the tubular member 53, and the turbine rotor 33 is used as the cooling medium RA. Cooling.

  In the above configuration, the hollow portion 29 that is the inner space of the compressor rotor 11 can be utilized to cool the inside of the gas turbine. Therefore, the engine efficiency and life can be reduced while suppressing an increase in the size of the gas turbine 1. Etc. The performance is improved. Moreover, since the compressed air CA extracted from the compressor 3 is used as the cooling medium RA, the inside of the gas turbine 1 can be efficiently cooled without separately introducing air for cooling. Moreover, since the weight distribution of the pipe unit 51 is eccentric, by rotating integrally with the compressor rotor 11, as shown in FIG. 3 (a), the flange 55 of the pipe unit 51 is subjected to centrifugal force by the centrifugal force. 11 is pressed against the inner peripheral surface 11b in the eccentric direction P, so that it is stably supported by the compressor rotor 11 and does not swing.

  FIG. 5 is a longitudinal sectional view showing the gas turbine 1 according to the second embodiment of the present invention. In the second embodiment, the pipe unit 51 is formed not as the refrigerant passage of the first embodiment but as a seal air passage (seal air passage) SP that seals the central bearing 45, and will be particularly described below. Except for this point, the configuration is the same as that of the first embodiment.

  As shown in FIG. 6, which is an enlarged longitudinal sectional view of the periphery of the center bearing 45 in FIG. 5, the compressor rotor extending with the center bearing 45 is provided at the downstream end of the inner peripheral wall of the diffuser 21. A bearing housing 65, which is a first bearing case, covering the central portion in the axial direction of the portion 11B is connected by a bolt (not shown). Inside the bearing housing 65, a bearing box 67, which is a second bearing case, is provided. A bearing chamber 60 that houses the central bearing 45 is formed inside the bearing box 67 in the radial direction, and air seal mechanisms 69 and 69 are provided on both outer sides in the axial direction of the bearing chamber 60.

  The air seal mechanism 69 is a vent in which high-temperature air LA leaked from the compressor 3 and high-temperature gas LG leaked from the combustor 5 communicated with the outside of the engine, which is a space between the bearing housing 65 and the bearing box 65. This is a seal mechanism for preventing the air from flowing into the bearing chamber 60 via the chamber 71.

  In the compressor rotor extending portion 11 </ b> B, a through hole penetrating from the hollow portion 29 to the air seal mechanism 69 is provided as a seal air introduction path 79 that allows the hollow portion 29 and the air seal mechanism 69 to communicate with each other. In addition, the rear end portion 51b of the tubular member 53 of the pipe unit 51 is closed, and air that is a radial through hole is formed in the peripheral wall of the portion inserted into the hollow portion 29 of the compressor rotor extension portion 11B. A hole 81 is provided.

  The compressed air CA extracted from the compressor 3 through the compressed air extraction passage 63 in FIG. 5 passes through the seal air passage SP and then passes through the air outlet hole 81 and the seal air introduction passage 79 shown in FIG. The air seal mechanism 69 is supplied as seal air SA. A part of the sealing air SA supplied to the air sealing mechanism 69 flows out into the vent chamber 71 and prevents high temperature air from flowing into the bearing chamber 60.

  Thus, according to the gas turbine 1 which concerns on 2nd Embodiment, since the hollow part 29 which is the inner space of the compressor rotor 11 can be utilized, the inside of a gas turbine can be sealed, so the gas turbine 1 While suppressing an increase in the size of the engine, performance such as engine efficiency and life is improved. Since the compressed air CA extracted from the compressor 3 is used as the seal air SA, it is possible to efficiently seal the inside of the gas turbine 1 without separately introducing air for cooling or sealing.

  FIG. 7 is a cross-sectional view showing a gas turbine according to a third embodiment of the present invention. In the third embodiment, a measurement cable 85 is extended inward of the pipe unit 51, and has the same configuration as that of the first embodiment except for the points specifically described below. .

  In the present embodiment, the pipe unit 51 extends from the front end portion 11 a to the rear end portion 11 c of the compressor rotor 11. The cable 85 is a cable for measuring the temperature of the turbine rotor 33 to which the moving blades of the turbine 7 are attached and taking out the measurement signal to the outside. That is, one end of the cable 85 is connected to the temperature sensor 87 attached to the turbine rotor 33, and the other end of the cable 85 is connected to the telemeter transmitter 89.

  The telemeter transmitter 89 is a device that wirelessly transmits a measurement signal. As shown in FIG. 8, which is an enlarged sectional view of the periphery of the front end portion 11 a of the compressor rotor 11 of FIG. 7, the front end of the compressor rotor 11 is provided. It is attached to an annular support 91 fixed together with a support member 56 and a bolt 90 to the portion 11 a and rotates together with the compressor rotor 11. The telemeter transmitter 89 has a transmission antenna 93 on its inner periphery. Further, on the radially inner side of the transmission antenna 93 of the telemeter transmitter 89, a reception antenna 95 of a telemeter receiver (not shown) is supported by the inner cowl 20 which is a non-rotating member of the compressor 3, and the transmission antenna The measurement signal of the temperature sensor 87 in FIG. 7 is transmitted to the telemeter receiver installed outside through the cable 85, the transmission antenna 93, and the reception antenna 95. Is done.

  In the present embodiment, the example in which the sensor connected to one end of the cable 85 is the temperature sensor 87 has been described. However, the measurement element connected to the cable 85 is not limited to this, and a strain sensor, a rotation sensor, or the like. Various measuring devices can be used. Further, the cable 85 is not limited to the measurement cable 85 described as the present embodiment, but for various purposes as required, for example, for transmission of control signals and power transmission of devices installed therein. It may be. By comprising in this way, the hollow part 29 which is the inner space of the compressor rotor 11 can be utilized effectively, and the high function and high performance of a gas turbine engine can be achieved.

  Since the cable 85 in the pipe unit 51 is not fixed in the pipe unit 51, the cable 85 swings in the tubular member 53 of the pipe unit 51 when rotating together with the compressor rotor 11 and the pipe unit 51. . However, since the weight distribution in the cross section of the pipe unit 51 is eccentric, the pipe unit 51 is prevented from swinging in the hollow portion 29 due to the influence of the cable 85 swinging around.

  Thus, by providing the pipe unit 51 in the inner space of the rotor and using it as a member for cable arrangement, the gas turbine 1 is improved in performance and function while suppressing an increase in the overall size of the gas turbine 1. Can be achieved.

  In the description of each of the above embodiments, the example in which the pipe unit 51 is provided in the hollow portion 29 of the compressor rotor 11 has been described. However, the pipe unit 51 may be replaced with or added to the compressor rotor 11. The turbine rotor 33 may be provided.

  As described above, the preferred embodiments of the present invention have been described with reference to the drawings, but various additions, modifications, or deletions can be made without departing from the spirit of the present invention. Therefore, such a thing is also included in the scope of the present invention.

DESCRIPTION OF SYMBOLS 1 Gas turbine engine 3 Compressor 5 Combustor 7 Turbine 11 Compressor rotor 23 Rotor stage 29 Hollow part (inner space of rotor)
51 Pipe unit 53 Tubular member 55 Flange 85 Cable SP Seal air passage RP Refrigerant passage RA Cooling air SA Seal air

Claims (5)

A hollow rotor comprising a plurality of rotor stages connected in the axial direction and forming at least one of a compressor and a turbine;
A pipe unit inserted axially into the inner space of the rotor;
With
A gas turbine engine in which a weight distribution in a cross section of the pipe unit is eccentric with respect to an axis of the rotor ;
The pipe unit has a tubular member and a flange that is provided on an outer periphery of the tubular member and fits to an inner peripheral surface of the rotor,
A gas turbine engine, wherein a weight distribution in a cross section of the flange is eccentric with respect to an axis of the rotor. The gas turbine engine according to claim 1 , wherein the pipe unit forms a passage for a cooling medium that cools the inside of the gas turbine engine. 3. The gas turbine engine according to claim 1 , wherein the pipe unit forms a seal air passage for sealing a bearing that rotatably supports the rotor. 4. The gas turbine engine according to claim 2 , wherein the rotor is a compressor rotor, and the cooling medium or the seal air is compressed air extracted from the compressor. The gas turbine engine according to claim 1 , wherein a cable is extended inward of the pipe unit.

Images