JPH076404B2 - gas turbine - Google Patents

Description

TECHNICAL FIELD The present invention relates to a gas turbine.

(Prior Art) As a conventional gas turbine, for example, there was one as shown in Fig. 5 (reference material: GAS TURBINE WORLD: March-Ap
ril 1987).

To explain this, the gas turbine 51 is composed of the basic components of a compressor 52, a combustor 59, and a turbine 53, and a rotating shaft 54 connecting the compressor 52 and the turbine 53 drives a load 56 via a speed reducer 55. Has become.

The heat exchanger (recuperator) 57 has a flow passage 57a through which high temperature exhaust gas discharged from the turbine 53 passes and a flow passage 57b through which low temperature compressed air discharged from the compressor 52 passes, as shown by an arrow in the figure. The structure is such that they oppose each other via a heat wall, and heat of exhaust gas discharged from the turbine 53 is recovered to reduce the fuel consumption rate.

(Problems to be Solved by the Invention) In such a regenerative gas turbine, it is necessary to provide a heat insulating material 61 for insulating the combustor 59, the turbine 51, the heat exchanger 57, and the duct 60 connecting these. However, the space taken up by the heat insulating material 61 causes not only an increase in size of the gas turbine but also an increase in the number of parts, resulting in an increase in cost.

The present invention aims to solve these conventional problems.

(Means for Solving the Problems) In order to achieve the above object, in the present invention, exhaust gas discharged from a turbine and compressed air sent from a compressor to a combustor are respectively passed to recover heat of the exhaust gas. In a gas turbine equipped with a heat exchanger, a combustor has a cylindrical liner that is detachably fitted in the middle of an outer chamber into which compressed air from the heat exchanger flows, and a duct that guides compressed air flowing out from the heat exchanger. Was connected to this liner, and the liner and the heat exchanger were integrated via a duct.

(Operation) Based on the above configuration, the combustor is provided with the cylindrical liner that is detachably fitted in the middle of the outer chamber.
It is possible to integrate the liner and the heat exchanger via the duct, which eliminates the need to provide a joint flange etc. in the duct, shortens the duct and places the combustor and the heat exchanger close to each other. As a result, the gas turbine can be made smaller and lighter.

By forming the liner in a cylindrical shape, even if the liner is deformed forever, the peripheral length of the fitting part does not change, so it can be easily fitted and good assembly is obtained. To be

(Embodiment) An embodiment of the present invention will be described below with reference to the accompanying drawings.

As shown in FIG. 1 and FIG. 2, respectively, the gas turbine 1
Consists of the basic components of the compressor 2, the combustor 3 and the turbine 4. The turbine rotor 11 driven by high temperature gas and the centrifugal compressor impeller 12 that pressurizes the low temperature gas are coaxially connected via a shaft 13. The shaft 13 is cantilevered via a pair of rolling bearings 15 and drives a load via a gear 14 formed at its tip.

In the combustor 3, the fuel injected from the fuel injection valve 6
The combustion gas that has combusted with the compressed air that is introduced into 35 and becomes high temperature gas, and the combustion gas that flows out from the combustor 3 is bent in the flow path 28 that is defined between the plenum chamber 27 and the heat insulating material 33, and then the turbine housing outer periphery A flow path defined on the spiral between the walls 32
The turbine rotor 11 is guided to the turbine rotor 11 through 29 and expands to impart a rotational force to the turbine rotor 11. In addition,
The heat insulating material 33 is provided so as to be joined to the flange 22 side, and insulates the combustion gas guided to the turbine rotor 11.

The high-temperature exhaust gas discharged from the turbine 4 flows into the heat exchanger (recuperator) 5 from the turbine housing 26 through the diffuser 25 as shown by the arrow in the figure, and recovers the heat of the exhaust gas.

The heat exchanger 5 has a flow passage (not shown) for passing the high-temperature exhaust gas sent from the turbine 4 formed in the rotation axis direction of the shaft 13, and is arranged along the flow direction of the exhaust gas discharged from the turbine 4. To be done. A passage through which the low temperature compressed air sent from the compressor 2 passes is formed so as to face the exhaust gas passage in parallel to each other via a heat transfer wall.

The heat exchanger 5 and the combustor 3 are arranged in parallel with each other, and a casing 21 that covers both the heat exchanger 5 and the combustor 3 is provided, and low-temperature compressed air discharged from the compressor 2 passes through the casing 21. It is guided to the heat exchanger 5.

The combustion gas from the combustor 3 passes through the turbine 4 and the heat exchanger 5
The heat is dissipated into the casing 21 in the process of flowing through the air. This heat dissipation is absorbed by the low temperature compressed air flowing in the casing 21 to improve the fuel consumption rate, and the combustor 3 to the turbine 4
Also, the heat insulating material provided in the heat exchanger 5 in the flow path of the combustion gas can be significantly reduced, and the gas turbine 1 can be made compact and lightweight.

The low temperature compressed air sent from the compressor impeller 12 is an annular passage formed in the flange 22 as shown by the arrow in the figure.
It flows through the casing 23 into the casing 21. The casing 21 is fastened to the outer peripheral end of the flange 22 via a plurality of bolts 24.

The heat exchanger 5 is formed with an inlet 5A for low-temperature compressed air that opens into the casing 21, and the compressed air that flows in from this inlet 5A and is heated through the heat exchanger 5 is bent by the header 5C. After that, it flows into the combustor 3 through the duct 38.

As shown in FIG. 3, in the combustor 3, a cylindrical inner chamber 36 and an outer chamber 34 are provided around a combustion tube 35 in concentric cross sections, and compressed air sent from the heat exchanger 5 is As shown by the middle arrow, the inner chamber 36 is detoured to be introduced from the entire circumference of the combustion cylinder 35.

The outer chamber 34 is divided into three parts, that is, a first liner 41, a second liner 42, and a third liner 43. It is also possible to integrate the second liner 42 and the third liner 43.

A cap 35 is fastened to one end of the first liner 41 via a flange 44 and a plurality of bolts 45, and one end of an inner chamber 36 is fixed to the inner peripheral surface thereof.

One end of the third liner 43 is tapered to form a combustion cylinder.
It is fixed to the outer peripheral tip of 35.

The second liner 42 has a duct connected to the outlet side of the heat exchanger 5.
38 is stuck. The duct 38 is formed in a frame shape having a quadrangular cross section, and a lower end 38b thereof is linearly joined to the heat exchanger 5 and fixed thereto by welding, while an upper end 38a thereof is fixed to the second liner 42.
It is curved and joined along the outer periphery of and is also fixed by welding.

As shown in FIG. 4, annular locking rings 46 and 47 are fixed to the outer peripheral surfaces of the first liner 41 and the third liner 43, respectively. Each locking ring 46, 47 is formed in a crank shape in cross section, and defines an annular groove 48, 49 between the first liner 41 and the second liner 42, and each annular groove 48, 49 of the second liner 42. Both ends are detachably fitted.

Next, the operation will be described.

By forming the second liner 42 in a cylindrical shape, even if the second liner 42 and the annular grooves 48, 49 are slightly deformed, the peripheral lengths of the second liner 42 and the annular grooves 48 do not change, so that they can be fitted easily. It is possible to secure good assembly property.

Since the combustor 3 is provided with the cylindrical second liner 42 that is detachably fitted in the middle of the outer chamber 34, the second liner 42 and the heat exchanger 5 can be integrated via the duct 38. Becomes As a result, it is not necessary to provide a flange or the like in the middle of the duct 38.

Since there is no flange in the middle of the duct 38 as described above, the combustor 3 and the heat exchanger 5 arranged in parallel can be brought close to each other, and the casing 21 that covers them can be miniaturized to the outside. Heat dissipation can be further reduced.

On the other hand, when the joint flange is provided in the middle of the duct 38, the distance between the combustor 3 and the heat exchanger 5 arranged in parallel becomes large, which causes the gas turbine 1 to be upsized and the weight to be increased. Since the space between the combustor 3 and the heat exchanger 5 is narrow, there is a problem that assembly is poor.

As a countermeasure against this, it is conceivable to separate the middle of the duct 38 so as to be detachably fitted, but in that case, it is possible to secure the shape accuracy of the duct fixed to the heat exchanger 5 having a thin wall structure. However, when fitting ducts having a quadrangular cross-section, it is difficult to assemble even if there is a slight deformation, which causes a problem that maintainability is deteriorated.

Although the counterflow heat exchanger 5 is used in this embodiment, a crossflow heat exchanger in which the exhaust gas and the low temperature compressed air intersect at right angles may be used, and in that case, the opening to the combustor 3 is used. The part becomes relatively large.

(Effects of the Invention) As described above, according to the present invention, the combustor is provided with the cylindrical liner detachably fitted in the middle of the outer chamber into which the compressed air from the heat exchanger is introduced, and the combustor is discharged from the heat exchanger. Connect a duct that guides compressed air from the side of this liner,
Since the liner and heat exchanger are integrated via a duct, there is no need to provide a flange joint where the accuracy of the shape is easily changed in the middle of a duct with a rectangular cross section, facilitating processing and assembly, and making the heat exchanger and combustor close to each other. In addition, the gas turbines can be arranged in parallel, the size and weight of the gas turbine can be reduced, and the heat radiation amount can be reduced to improve the fuel consumption rate.

[Brief description of drawings]

1 is a side sectional view of a gas turbine showing an embodiment of the present invention, FIG. 2 is a front sectional view of the same, FIG. 3 is an exploded perspective view,
FIG. 4 is a sectional view of a main part. FIG. 5 is a sectional view showing a conventional example. 1 ... Gas turbine, 2 ... Compressor, 3 ... Combustor, 4 ... Turbine, 5 ... Heat exchanger, 34 ... Outer chamber, 38 ... Duct, 42 ... Second liner.

Claims (1)

[Claims] 1. A gas turbine comprising a heat exchanger for recovering heat of exhaust gas through exhaust gas discharged from a turbine and compressed air sent from a compressor to a combustor, wherein the combustor is a heat exchanger. Equipped with a cylindrical liner that is removably fitted in the middle of the outer chamber into which compressed air from the heat exchanger is introduced, and a duct that guides the compressed air that flows out from the heat exchanger is connected to this liner to connect the liner and the heat exchanger to the duct. Gas turbine characterized by being integrated via.