US3715886A - Gas turbine installation with a centrifugal fluid vanes compressor - Google Patents

Gas turbine installation with a centrifugal fluid vanes compressor Download PDF

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Publication number
US3715886A
US3715886A US00132106A US3715886DA US3715886A US 3715886 A US3715886 A US 3715886A US 00132106 A US00132106 A US 00132106A US 3715886D A US3715886D A US 3715886DA US 3715886 A US3715886 A US 3715886A
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fluid
gas
compressor
gas turbine
rotor
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US00132106A
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Staveren P Van
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases

Definitions

  • 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 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • the rotor is driven by the tangentially directed fluid.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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).
  • 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
  • FIG. 4 is a perspective view of a cylindrical adjustment device.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • FIG. 2 a gas turbine installation is shown schematically in which the centrifugal fluid vanes compressor as described above is applied.
  • a turbine 26 On one and the same shaft 25 a turbine 26, a coin pressor 27 and a fluid pump 28 are mounted.
  • compressor 27 gas for instance, air
  • compressor 27 gas for instance, air
  • 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.
  • gas turbine 26 the compressed heated gas gives off power, which is used to drive compressor 27 and fluid pump 28.
  • fluid pump 28 the fluid is raised in pressure and led through fluid turbine 33.
  • 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.
  • 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.
  • a gas turbine 48 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.
  • 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
  • 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.
  • 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.
  • adjusting device 65 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.
  • 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

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
US00132106A 1970-04-07 1971-04-07 Gas turbine installation with a centrifugal fluid vanes compressor Expired - Lifetime US3715886A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
NL707004991A NL144709B (nl) 1970-04-07 1970-04-07 Gasturbine-installatie met een centrifugaal-vloeistofvanencompressor.

Publications (1)

Publication Number Publication Date
US3715886A true US3715886A (en) 1973-02-13

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ID=19809793

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Application Number Title Priority Date Filing Date
US00132106A Expired - Lifetime US3715886A (en) 1970-04-07 1971-04-07 Gas turbine installation with a centrifugal fluid vanes compressor

Country Status (11)

Country Link
US (1) US3715886A (OSRAM)
JP (1) JPS5018522B1 (OSRAM)
BE (1) BE765365A (OSRAM)
CA (1) CA928085A (OSRAM)
CH (1) CH536434A (OSRAM)
DE (1) DE2117066C3 (OSRAM)
FR (1) FR2085890B1 (OSRAM)
GB (1) GB1316184A (OSRAM)
NL (1) NL144709B (OSRAM)
SE (1) SE369615B (OSRAM)
SU (1) SU396879A3 (OSRAM)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109268141A (zh) * 2018-10-30 2019-01-25 常胜 多燃料发动机

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL6903027A (OSRAM) * 1969-02-26 1970-08-28

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109268141A (zh) * 2018-10-30 2019-01-25 常胜 多燃料发动机

Also Published As

Publication number Publication date
GB1316184A (en) 1973-05-09
FR2085890A1 (OSRAM) 1971-12-31
DE2117066B2 (de) 1973-04-26
DE2117066A1 (de) 1971-10-21
NL7004991A (OSRAM) 1971-10-11
JPS5018522B1 (OSRAM) 1975-06-30
CH536434A (de) 1973-04-30
CA928085A (en) 1973-06-12
NL144709B (nl) 1975-01-15
FR2085890B1 (OSRAM) 1976-03-19
SU396879A3 (OSRAM) 1973-08-29
DE2117066C3 (de) 1973-11-15
BE765365A (nl) 1971-10-06
SE369615B (OSRAM) 1974-09-09

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