JPH04246300A - Compressor for gas turbine - Google Patents

Abstract

PURPOSE:To reduce the air energy loss by connecting a fore stage compression part and an aft stage compression part through an air collector having a wide sectional area and a large capacity and installing a rectifying guide on the suction side in the aft stage. CONSTITUTION:A gas turbine is equipped with a centrifugal type fore stage compression part 11 and a centrifugal type aft stage compression part 12, and an air collector chamber 50 is formed between both. Gas is compressed by the revolution of the fore stage compression part 11 and introduced into the air collector chamber 50 from a discharge part 11a. In this case, low speed is generated, and the kinetic energy is converted to the pressure energy, and the energy loss due to the conduit resistance is reduced extremely. The gas is guided into the suction part 12a of the rear stage compression part 12 by a rectifying guide 51. Accordingly, the loss of the air energy can be reduced markedly.

Description

[Detailed description of the invention]

0001

[Industrial Application Field] The present invention relates to a gas turbine compressor that has a centrifugal front compression section and a centrifugal rear compression section, and further compresses air compressed in the front compression section in the rear compression section. Regarding.

0002

[Prior Art] As a turbine compressor equipped with two stages of centrifugal compression sections, for example, the Utility Model Application Publication No. 2-110237
A hairpin-curved air passage, which is simply an air flow passage, is continuously formed between the discharge part of the front-stage compression part and the suction part of the latter-stage compression part.

0003

[Problems to be Solved by the Invention] With the structure of this conventional example, the air that has obtained a large amount of kinetic energy and has a high flow velocity in the first stage compression section is not converted into pressure energy on the way, and is transferred to the second stage compression section. Since it is continuously supplied to the suction section, energy loss due to pipe resistance in the air passage between the front-stage compression section and the rear-stage compression section is large, and a problem remains in terms of energy efficiency.

0004

[Means for solving the problem] A centrifugal front-stage compression section,
In a gas turbine compressor that has a centrifugal post-compression section and compresses the air compressed in the pre-compression section further in the post-compression section, the space between the air discharge section of the pre-compression section and the air suction section of the post-compression section are connected by an air collector chamber with a large flow cross-sectional area and a large volume, and the flow of compressed air in the air collector chamber is directed to the air intake direction of the rear compression section to the air collector chamber on the air intake section side of the rear compression section. This is a gas turbine compressor characterized by being provided with a rectifying guide for rectifying the flow.

[0005]

DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 shows an overall schematic diagram of a gas turbine equipped with a compressor according to the present invention, and the overall structure will be briefly described assuming that the left side of the figure is the front side. The gas turbine includes a compressor A, a turbine section B, and a combustor C in order from the front side, and also includes a rotor shaft 1 extending in the front-rear direction at the center of rotation. The front compressor A has an outer shell composed of an intake housing 3, a compressor bearing housing 4, an intermediate housing 5, etc., and includes a centrifugal front compression section 11 and a rear compression section 12.
2 are meshed with each other via a meshing portion 10 so as to rotate integrally with each other, and are operatively connected via a seal housing 15 to a disk 19 for supporting a rotor blade of a rear turbine section B.

A scroll chamber 16 is provided in the turbine casing 13 so as to surround the rotor shaft 1, and the radially outer end of the scroll chamber 16 is connected to the combustion gas of the combustor C via a combustion gas communication pipe 8. Connected to the gas discharge part. A combustion gas passage S is provided on the axis side of the scroll chamber 16, and the combustion gas passage S includes turbine blades including a plurality of rotor blades (moving blades) 17 for a plurality of turbines and a plurality of nozzle blades (stationary blades) 18. section is arranged. A discharge port on the axis side of the scroll chamber 16 opens at the exhaust gas upstream end of the combustion gas passage S, and the combustion gas flows from the discharge port to the combustion gas passage S.
supplied within.

Each of the rotor blades 17 is supported by the outer peripheral end of a disc 19 for supporting the rotor blade, and the discs 19 are connected to each other via a meshing part so as to be rotatable together, and are connected to a rear coupling 25. The coupling 25 is interlocked and spline-fitted to the outer peripheral surface of the rear end of the rotor shaft 1 so as to rotate together with the rotor shaft 1. Each nozzle blade 18 is fixedly supported by a cylindrical turbine case 20 for supporting the nozzle on the outer circumferential side of the blade. A containment ring (cylindrical partition wall) 21 is arranged to prevent scattering.

A cylindrical exhaust diffuser 28 for decelerating exhaust gas is attached to the opening of the turbine casing 13, and communicates with the exhaust gas outlet side of the combustion gas passage S, and is connected to the downstream side of the exhaust diffuser 28. The end portion is connected to, for example, an exhaust muffler.

The rotor shaft 1 has a turbine-side rear end supported by a bearing housing 35 via a turbine-side bearing 23.
The inner peripheral side of the disk 19 extends forward toward the compressor A side, passes through the compressor A, etc., and is used as a power output shaft for driving a load such as a generator. A front end portion of the rotor shaft 1 on the compressor side is supported by the inner peripheral portion of the compressor bearing housing 4 via a compressor side rotation bearing 24 and a thrust bearing 38.

In FIG. 2, curved shrouds 38 and 39 are disposed on the radially outer side of each compression section 11 and 12, respectively.
Curved blade portions 40 and 41 are formed along the shape of 39. A front air passage 44 is formed at the front end of the intermediate housing 5 by the front partition 32 and the like and extends radially outward from the outer end of the front blade 40. It is bent axially rearward by the bending guide portion 47 and communicates with the upper end portion inside the intermediate housing 5 .

A rear partition wall 3 is provided at the rear end of the intermediate housing 5.
A rear stage air passage 45 extending radially outward from the outer end of the rear stage blade portion 41 is formed between the rear stage air passage 45 and the rear stage air passage 45, and the radially outer end of the rear stage air passage 45 communicates with the compressed air chamber 30. There is. The inside of the intermediate housing 5 is formed as an air collector chamber 50 having a large flow cross-sectional area and a large volume, and converts the kinetic energy of the air discharged from the front air passage 44 into pressure energy, thereby slowing down the flow velocity of the air. It is formed to have a volume of approximately

The radially inner end of the air collector chamber 50 communicates with the air suction section 12a of the rear compression section 12, and the air flow inside the air collector chamber 50 is connected to the rear compression section 12.
A plurality of rectifying guides 51 are arranged to rectify the air in the air intake direction T. The rectifying guide 51 is fixed to the rear shroud 39 via a bracket 52. Further, a plurality of axial guide plates 53 are arranged in the air discharge section 11a of the pre-stage compression section 11 to guide the flow of air in the axial direction.
The guide plate 53 is fixed to the bending guide portion 47.

[0013] The operation will be explained. In FIG. 1, compressor A
The air supplied to the intake manifold 3 is first compressed by the rotation of the front-stage compression section 11, and then passes through the front-stage air passage 44.
The air flows outward, is converted into an axial flow by the guide portion 47 in FIG. 2, is rectified by the guide plate 53, and is discharged from the discharge portion 11a into the air collector chamber 50. In the compression stage of the pre-compression section 11, the air gains a large amount of kinetic energy, has a high flow rate, and is discharged into the air collector chamber 50, which has a large volume.

[0014] Approximately 50% of the kinetic energy is
is lost, but as the flow becomes slower, most of the remaining kinetic energy is converted into pressure energy,
In the state of pressure energy, the suction section 12 of the rear compression section 12
Leading to a. Air collector chamber 5 with low flow rate and wide flow cross section
0, energy loss due to pipe resistance is extremely small, and pressure loss is approximately equivalent to the dynamic pressure in the front stage. That is, pressure energy with less energy loss (bending loss, vortex loss, etc.) due to pipe resistance etc. can be guided to the suction section 12a of the latter stage compression section 12. Incidentally, the energy loss due to conduit resistance was less than 1%.

The air further compressed in the rear stage compression section 12 enters the compressed air chamber 30 through the rear stage air passage 45. From here, it is sent to the combustor C in Figure 1, where it is mixed with fuel and used for combustion, and the combustion gas generated there is sent to the scroll chamber 1.
6 and is supplied to the combustion gas passage S. After rotating the rotor blades 17 of the turbine in the combustion gas passage S, the combustion gas is sent to an exhaust muffler or the like through an exhaust diffuser 28.

[0016]

As explained above, the present invention provides air flow between the discharge section 11a of the front-stage compression section 11 and the air suction section 12a of the rear-stage compression section 12 by the air collector chamber 50 having a large flow cross-sectional area and a large volume. A rectifying guide 51 is provided in the air collector chamber on the air suction side of the rear compression section 12 to rectify the flow of pressurized air in the air collector chamber 50 in the air intake direction of the rear compression section 12. Air flows at a low flow rate in the air collector chamber 50 with a large flow rate, and energy loss due to pipe resistance can be extremely reduced, improving energy efficiency and compression performance.

[Brief explanation of the drawing]

FIG. 1 is a schematic vertical cross-sectional view of the entire gas turbine to which the present invention is applied.

FIG. 2 is an enlarged view of part II in FIG. 1.

[Explanation of symbols]

1 Rotor shaft 11 Pre-stage compression section 11a Discharge part 12　Late stage compression section 12a Suction part 50 Air collector room 51 Rectification guide

Claims (1)

[Claims] Claim 1: A gas turbine compressor having a centrifugal front-stage compression section and a centrifugal rear-stage compression section, in which the air compressed in the front-stage compression section is further compressed in the rear-stage compression section. Between the air discharge part and the air suction part of the latter stage compression part,
Connected by an air collector chamber with a wide flow cross section and large volume, the flow of compressed air in the air collector chamber is rectified in the air intake direction of the rear compression section to the air collector chamber on the air intake section side of the rear compression section. A gas turbine compressor characterized by being provided with a rectification guide.