US3715886A

US3715886A - Gas turbine installation with a centrifugal fluid vanes compressor

Info

Publication number: US3715886A
Application number: US00132106A
Authority: US
Inventors: Staveren P Van
Original assignee: Individual
Current assignee: Individual
Priority date: 1970-04-07
Filing date: 1971-04-07
Publication date: 1973-02-13
Anticipated expiration: 1990-02-13
Also published as: DE2117066B2; GB1316184A; DE2117066C3; FR2085890A1; BE765365A; NL144709B; SE369615B; CA928085A; NL7004991A; DE2117066A1; FR2085890B1; JPS5018522B1; CH536434A; SU396879A3

Abstract

A gas turbine installation comprising a gas turbine the shaft of which is coupled with a compressor and a fluid pump, which drives a fluid turbine.

Description

United States Patent Staveren GAS TURBINE INSTALLATION WITH A CENTRIFUGAL FLUID VANES COMPRESSOR Inventor: Pieter Van Staveren, l9, Wilhelminasingle, Pijnacker, Netherlands Filed: April 7, 1971 Appl. No.: 132,106

Foreign Application Priority Data April 7, 1970 Netherlands ..70/0499l US. Cl ..60/39.l8 R, 60/39.45, 60/221 Int. Cl. ..F02c 3/02 Field of Search....60/39.l8 R, 39.18 A, 39.18 B,

[56] References Cited UNITED STATES PATENTS 3,386,246 6/l968 Sugimura ..60/39.l8 R 3,367,563 2/1968 I-Iertzberg et al. ..60/39.45 2,968,914 l/l96l Birmann ..60/39.18 R

Feb. 13, 1973 FOREIGN PATENTS OR APPLICATIONS 88,127 8/1896 Germany ..'....415/98 Primary ExaminerCarlton R. Croyle Assistant ExaminerWarren Olsen Attorney-Watson, Cole, Grindle & Watson 5 7 ABSTRACT A gas turbine installation comprising a gas turbine the shaft of which is coupled with a compressor and a fluid pump, which drives a fluid turbine.

The improvement consists in that in the gas turbine cycle a centrifugal fluid vanes compressor is incorporated, which on the one hand is connected to the compressor for the supply of gas and on the other hand is connected to the exhaust of the hydraulic turbine for the supply of the fluid forming the fluid vanes, which fluid also drives the rotor.

The efficiency of the installation and its velocity in response to changes in load are considerably improved.

1 Claim, 4 Drawing Figures FLUID VANES COMPRESSOR FLUID FLOW GAS FLOW PATENIEUFEB 1 3 197a SHEET 1 OF 2 INVENTOR.

PATENIED FEB 13 I975 SHEET 2 OF 2 FLUID VANES COMPRESSOR FLUID FLOW as I FIG.2

FlG.3

INVENTOR BY J GAS TURBINE INSTALLATION WITH A CENTRIFUGAL FLUID VANES COMPRESSOR The invention relates to a gas turbine installation, equipped with at least a compressor, at least a heatexchanger for transmitting heat from the exhaust gases of the gas turbine to the compressed energy-medium and at least a combustion room with an adjustable fuel supply.

It is known in the art that a heat exchanger in a gas turbine installation is only essential for a high efficiency. Consequently a gas turbine installation provided with a heat exchanger yields an economically acceptable efficiency, but it is exceptionally slow in varying the power delivered.

This slowness can entirely be eliminated, when in the gas turbine installation a centrifugal fluid vanes compressor is applied, such as is described in the pending U.S. Pat. application Ser. No. 14,590, now U.S. Pat. No. 3,668,867 dated June 13, 1972 and filed by the same applicant. Of this applied centrifugal fluid vanes compressor, whose rotor is driven by the gas turbine, at least one of the walls bounding the compressor room is freely rotatable and provided with blades alongside its periphery, hereinafter further referred to as secondary rotor. An auxiliary pump also driven by the gas turbine carries the fluid to the fluid vanes compressor, in which an effluvium, for instance air, is compressed, separated from the fluid forming the vanes and is carried to the gas turbine via a heat exchanger and a combustion chamber. The separated fluid makes the secondary rotor rotate. In the process the dimensions are chosen such that the useful power delivered by the gas turbine becomes available at the shaft of the secondary rotor, that is that the power still present in the fluid at the end of the compression process, apart from some losses, consequently is equal to the power to be delivered by the gas turbine. Adjustment of power delivered is then effected by adjusting the supply of fluid to the fluid vanes compressor. In doing so, the exhaust temperature of the gas turbine is kept constant under all conditions in a way known in the art by an automatic adjustment of the supply of fuel to the combustion chamber.

Though in the above gas turbine installation the effect of the thermic slowness of the heat exchanger upon the controllability of the installation is entirely eliminated, its pressure ratio is restricted and as a result of this the dimensions are becoming too large for a justified efficient application of great powers.

It is an object of the invention, to raise the efficiency of a gas turbine installation without energy being lost.

It is a further object of the invention to increase the velocity of the response to changes in the load and the adjustment of a gas turbine installation.

It is another object of the invention to provide a special method of adjustment for eliminating the thermic slowness of the heat exchanger.

For these purposes, in a gas turbine installation with at least a compressor, a centrifugal fluid vanes compressor is applied, such as is described in the pending U.S. Pat. application Ser. No. 129,803 filed Mar. 31, 1971 by the present applicant, as a result of which the advantage is obtained that upon designing for great powers a very compact construction can be realized.

In this centrifugal fluid vanes compressor the fluid is tangentially supplied to the fluid entrance opening of the rotor, which entrance opening is situated substantially in the same circumferential plane of the rotor as the fluid discharge openings of the jets, while the absolute entrance velocity of the fluid to the rotor is substantially equal to the local circumferential speed of the rotor. In the process, the rotor is driven by the tangentially directed fluid.

Besides the advantage of the enhanced efficiency of the fluid vanes compressor, the gas turbine installation according to the invention has the surprising advantage that by a special adjustment the exhaust temperature of the gas turbine, so also the temperature of the hot side of the heat exchanger, is kept constant under all conditions of loading. By keeping, in a way known in the art, the exhaust temperature at the cold side of the heat exchanger, which is the sameas the exhaust temperature of the fluid vanes compressor, also constant by coolers in the fluid stream, the thermic slowness of the heat exchanger is completely eliminated, so that such a gas turbine installation has a very quick response.

It is characterized in that the shaft of at least one gas turbine that comprises at least one stage is coupled with at least one compressor and at least one fluid pump, which drives a fluid turbine and in the gas turbine cycle at least one centrifugal fluid vanes compressor, whose rotor is driven by the fluid and which has been incorporated as the last compression stage and which on the one hand is connected to the compressor for the supply of the effluvium to be compressed further and on the other hand via a supply adjustment incorporated in the fluid supply, is connected to the exhaust of the fluid turbine for the supply of the fluid forming the fluid vanes and in that the useful power is taken from the shaft of the fluid turbine.

The adjustment of the supply of fluid to the fluid vanes compressor can be realized in different ways.

Advantageously this adjustment comprises an adjustable cylindrical shutter provided around the fluid entrance opening of the rotor.

The control of the power of the gas turbine installation is effected in a simple way by means of a combined adjustment of the supply of fuel to the combustion chamber and the supply of fluid to the rotor of the fluid vanes compressor, so that the exhaust temperature of the gas turbine can be kept constant under all conditions of loading.

If the control of the power of the gas turbine installation is effected by the adjustment of the supply of fuel to the combustion chamber, then at the same moment a deviation of the gas turbine exhaust temperature is automatically corrected by an adjustment of the supply of fluid to the rotor of the fluid vanes compressor.

For when the turbine exhaust temperature is too high, the supply of fluid to the rotor of the fluid vanes compressor is increased, the pressure ratio is raised, so that more gas flows through the gas turbine and consequently the temperature decreases. The reverse takes place, when the gas turbine exhaust temperature is too low.

If the control of the power of the gas turbine installation is effected by adjustment of the supply of fluid to the rotor of the fluid vanes compressor, then at the same moment a deviation in in the gas turbine exhaust temperature is automatically corrected by adjustment of the supply of fuel to the combustion chamber, in other words, if the gas turbine exhaust temperature is too low, the supply of fuel is increased or vice versa, when the exhaust temperature is too high then the supply of fuel is decreased.

In the drawings a gas turbine installation according to the invention, is shown; the set-up of the components is only an example of an embodiment.

Per se it is not essential that the compressed effluvium is first compressed in a compressor and then in a fluid vanes compressor, the reverse is also possible, just as application of still more compression stages. In order to obtain a rapid controliability of the gas turbine installation, however, it is necessary that as the last stage of compression :1 fluid vanes compressor is applied.

It is not only possible that in the gas turbine: installation the fluid turbine is placed after the pump, but also before the pump, for instance in a closed gas turbine system, in which the whole is under overpressure, and finally also between two pumps.

The gas turbine (axial or radial) can consist of one stage, which drives the compressor (axial or radial) and the pump, but also of several stages in a construction with a single-shaft drive, while a construction with a multi-shaft drive is also possible, for example one for the compressor(s) and one for the pump(s).

The invention will be further elucidated below with reference to the drawings in which by way of example an embodiment is shown schematically.

Thereby:

FIG. 1 is a sectional view through a centrifugal fluid vanes compressor;

FIG. 2 is a gas turbine installation that is schematically shown;

FIG. 3 is a half section of a gas turbine installation, and

FIG. 4 is a perspective view of a cylindrical adjustment device.

In FIG. 1 an embodiment is shown of a centrifugal fluid vanes compressor in accordance with the aforementioned pending application Ser. No. 129,803.

This consists of a compressor housing 1 that is assembled with fluid reservoir 2. Rotor 3, which has its bearings centrally in the compressor housing, is provided with blades 6 for sucking, via a sucking nozzle 7, for an effluvium to be compressed.

Rotor 3 further is provided with jets 8, which link up directly with an annular slit 9 arranged in the rotor, in which slit blades 10 are provided and in which the fluid is distributed over jets 8. Around rotor 3 an annular fluid chamber 11 is situated with a fluid discharge 12 provided alongside the inner diameter and arranged opposite to intake 18 of annular slit 9. In discharge slit l2 guiding blades 13 are provided, which with respect to rotor 3 are tangentially directed in its direction of rotation. Rotor 3 is driven by the tangentially directed fluid.

Besides, fluid chamber 11 is connected to a supply duct 14, which via an adjustment device 15 is coupled with a pump 16, which is connected to fluid reservoir 2 via pump duct 17.

The compressor room within which the fluid vanes are formed is bounded by walls and 21, surrounded by a collecting channel 22, which is in open connection with fluid reservoir 2.

In a way known in the art the compressed gases are separated in fluid reservoir 2 with the aid of partitions 23 and discharged via exhaust 24.

According to the invention, a considerable increase in efficiency is obtained, without energy being lost, because fluid entrance opening 18 of rotor 3 is situated substantially in the same circumferential plane of the rotor as discharge openings 19 of jets 8 and because the fluid is supplied tangentially, as much as possible, with an absolute entrance velocity that is substantially equal to the local circumferential speed of the rotor.

In FIG. 2 a gas turbine installation is shown schematically in which the centrifugal fluid vanes compressor as described above is applied.

On one and the same shaft 25 a turbine 26, a coin pressor 27 and a fluid pump 28 are mounted.

By compressor 27 gas, for instance, air, is sucked via supply 29 and raised in pressure. The compressed gas is led to fluid vanes compressor 31 via discharge 30. Fluid pump 28 supplies fluid to fluid turbine 33 via discharge 32. From there the fluid is carried to fluid vanes compressor 31 via exhaust 34. The compressed gas is still further compressed by the fluid vanes formed, separated from the fluid and lead through discharge 35 to intake 38 of gas turbine 26 via heat exchanger 36 and combustion chamber 37.

Combustion chamber 37 is connected to a fuel supply duct 39, in which an adjustment device 40 is incorporated. Exhaust 41 of gas turbine 26 discharges the used hot gas via heat exchanger 36. The fluid that is separated in fluid vanes compressor 31, from the gas compressed is collected in fluid reservoir 42 and fed back to fluid pump 28 through discharge 43 via a cooler 44.

The fluid vanes compressor is an isothermic compressor. With these types of compressors all compression labor must be discharged as heat, which consequently is effected in one or more coolers.

In gas turbine 26 the compressed heated gas gives off power, which is used to drive compressor 27 and fluid pump 28. By fluid pump 28 the fluid is raised in pressure and led through fluid turbine 33.

In this fluid turbine 33 the fluid gives off part of the power administered in fluid pump 28. This turbine power now is available as useful power of the gas tur bine installation and can be taken off from fluid turbine shaft 45. In fluid supply 34 towards fluid vanes compressor 31 an adjusting device is incorporated which adjusts the extent of the flowing fluid.

The power of the gas turbine installation is controlled by a combined adjustment of the fuel supply to combustion chamber 37 via adjustment device 40 and of the fluid supply to the rotor of fluid vanes compressor 31 via adjusting device 46.

In FIG. 3 a half section is shown of a gas turbine installation according to the invention, from which it appears clearly how compact the whole set-up can be constructed.

On one and the same shaft 47 a gas turbine 48, a compressor 49 (here drawn as a centrifugal compressor) and a fluid pump 50 are provided.

From compressor 49 the compressed gas is carried to centrifugal fluid vanes compressor 54 via bypass channel 51 to gas inlet 52 of rotor 53.

From fluid chamber 55 fluid is, supplied to fluid pump 50 via annular chamber 56 which is provided with blades. After having been raised in pressure, the fluid is led through fluid turbine 57 and then into annular fluid chamber 58 of fluid vanes compressor 54, of

which fluid chamber supply slit 59, which is arranged alongside the inner diameter, is provided with guiding blades 60 which are tangential with respect rotor 53 and in its direction of rotation. Fluid supply slit 59 is arranged opposite to the intake opening of annular slit 61, provided with blades 62 and in which the fluid is distributed over jets 63, which are communicating with annular slit 61. In compressor room 64 the fluid vanes are formed and the gas supplied by compressor 49 is compressed still further, separated fromthe fluid and in a way known in the art supplied to the intake of gas turbine 48 via a heat exchanger and a combustion chamber both of which are not shown in this drawing.

Between fluid supply slit 59 and the entrance opening of annular slit 61 adjusting device 65 is provided, which adjusts the passage of fluid to the entrance opening of annular slit 61.

The adjusting device can be constructed as a cylindrical shutter provided around the rotor, for instance a rotary sliding sleeve, such as is shown in perspective in FIG. 4.

The efficiency of the gas turbine installation as described above can still be further increased when in the closed pump circuit a fluid with a high boilingpoint, for instance oil, is applied.

Since it is possible to construct the entire gas turbine installation very compact, as well as because of the very high efficiency and the very rapid response to changes in load and modifications of the adjustment, such a gas turbine installation is in particular suitable for traction purposes,

lclaim:

1. A gas turbine installation, comprising a gas turbine, a compressor unit for compressing gas, a heat exchanger for transferring heat from the exhaust gases of the gas turbine to the compressed gas, a combustion chamber for heating the compressed gas and connected with a fuel duct comprising an automatic control of the fuel supply for keeping the turbine outlet temperature constant, at least one fluid pump coupled with the shaft of the gas turbine and a hydraulic turbine and driven by the fluid pump, the improvement comprising in that in the gas turbine cycle at least one centrifugal fluid vanes compressor is applied, said fluid vanes compressor comprising a housing having a pair of spaced parallel walls with an intake for the gas and an outlet for the compressed gas, in the center of the housing a driven rotor being provided with blades for suctioning the gas and provided with jet channels for forming the fluid vanes, wherein the fluid entrance opening of the rotor is located substantially in the same circumferential plane of the rotor as the discharge openings of the jet channels, and wherein around the rotor opposite the fluid entrance opening an annular fluid chamber is provided that is connected to a fluid supply duct, the annular outlet of the fluid chamber being provided with guiding blades, which are tangentially directed to a maximum with respect to the rotor in its direction of rotation, said centrifugal fluid vanes compressor being incorporated as the last compression stage and which via a gas duct is connected to the compressor unit for the supply of gas and which via a fluid duct is connected to the exhaust of the hydraulic turbine for the supply of the fluid for forming the fluid vanes, and control means for the ad'ustment of the fluid supply bein incorporated in the uid duct connected to said flui vanes compressor, and the useful power being taken off from the shaft of the hydraulic turbine.

Claims

1. A gas turbine installation, comprising a gas turbine, a compressor unit for compressing gas, a heat exchanger for transferring heat from the exhaust gases of the gas turbine to the compressed gas, a combustion chamber for heating the compressed gas and connected with a fuel duct comprising an automatic control of the fuel supply for keeping the turbine outlet temperature constant, at least one fluid pump coupled with the shaft of the gas turbine and a hydraulic turbine and driven by the fluid pump, the improvement comprising in that in the gas turbine cycle at least one centrifugal fluid vanes compressor is applied, said fluid vanes compressor comprising a housing having a pair of spaced parallel walls with an intake for the gas and an outlet for the compressed gas, in the center of the housing a driven rotor being provided with blades for suctioning the gas and provided with jet channels for forming the fluid vanes, wherein the fluid entrance opening of the rotor is located substantially in the same circumferential plane of the rotor as the discharge openings of the jet channels, and wherein around the rotor opposite the fluid entrance opening an annular fluid chamber is provided that is connected to a fluid supply duct, the annular outlet of the fluid chamber being provided with guiding blades, which are tangentially directed to a maximum with respect to the rotor in its direction of rotation, said centrifugal fluid vanes compressor being incorporated as the last compression stage and which via a gas duct is connected to the compressor unit for the supply of gas and which via a fluid duct is connected to the exhaust of the hydraulic turbine for the supply of the fluid for forming the fluid vanes, and control means for the adjustment of the fluid supply being incorporated in the fluid duct connected to said fluid vanes compressor, and the useful power being taken off from the shaft of the hydraulic turbine.