EP0409133A1 - Turboexpander mit hohem Wirkungsgrad - Google Patents

Turboexpander mit hohem Wirkungsgrad Download PDF

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Publication number
EP0409133A1
EP0409133A1 EP90113588A EP90113588A EP0409133A1 EP 0409133 A1 EP0409133 A1 EP 0409133A1 EP 90113588 A EP90113588 A EP 90113588A EP 90113588 A EP90113588 A EP 90113588A EP 0409133 A1 EP0409133 A1 EP 0409133A1
Authority
EP
European Patent Office
Prior art keywords
fluid
fluid flow
turboexpander
flow path
blades
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP90113588A
Other languages
English (en)
French (fr)
Other versions
EP0409133B1 (de
Inventor
James Bragdon Wulf
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Praxair Technology Inc
Original Assignee
Union Carbide Industrial Gases Technology Corp
Praxair Technology Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Union Carbide Industrial Gases Technology Corp, Praxair Technology Inc filed Critical Union Carbide Industrial Gases Technology Corp
Publication of EP0409133A1 publication Critical patent/EP0409133A1/de
Application granted granted Critical
Publication of EP0409133B1 publication Critical patent/EP0409133B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members

Definitions

  • This invention relates generally to the field of turboexpansion whereby fluid is expanded to produce useful work.
  • a high pressure fluid is often expanded, i.e. reduced in pressure, through a turbine to extract useful energy from the fluid and thus to produce work.
  • the high pressure fluid enters the turbine and passes through a plurality of passages defined by turbine blades which are mounted on an impeller hub which in turn is mounted on a shaft.
  • the fluid enters the blade passages and causes rotation of the impeller and ultimately leads to the recovery of energy and to the production of work from the spinning shaft.
  • turboexpanders generally handle large volumes of fluid, even a small increase in turbine efficiency will have a significant impact on operating results.
  • a method for operating a turboexpander having a rotatable assembly comprising a shaft, an impeller hub mounted on the shaft, and a plurality of blades on the impeller hub to form a plurality of fluid flow paths, each fluid flow path defined by the impeller hub surface and two adjacent blades, said method comprising:
  • a turboexpander having a rotatable assembly comprising a shaft, an impeller hub mounted on the shaft, and a plurality of blades on the impeller hub to form a plurality of fluid flow channels, each fluid flow channel defined by the impeller hub surface and two adjacent blades, characterized by:
  • turboexpander efficiency means the ratio of the actual to the ideal enthalpy difference between the inlet and the outlet conditions of the turboexpander.
  • mean streamline means the fluid flow path line which connects the midpoints of the fluid flow channel along the fluid flow path.
  • the term "meridional plane” means any plane that contains a point on the mean streamline of the fluid flow and the centerline of the impeller shaft.
  • substantially constant means within plus or minus 10 percent, preferably within plus or minus 5 percent.
  • fluid 14 such as nitrogen gas
  • the fluid inlet chamber 16 may be a volute or plenum that directs the fluid to inlet nozzles 17.
  • the rotatable assembly comprises shaft 5 and impeller hub 4 mounted on shaft 5.
  • a plurality of curved blades 6 are mounted on impeller hub 4 and, in this arrangement, shroud 8 covers the blades.
  • the arrangement results in a plurality of fluid flow paths 3 defined by the impeller hub surface, the shroud inner surface and two adjacent blades.
  • Shrouded impellers typically utilize a labyrinth seal 9 with seal face member 10 to prevent fluid bypass of the rotating assembly.
  • Non-shrouded or open impellers can be utilized with this invention and would utilize blade contours closely fitted to the stationary housing 18.
  • the stationary housing surface would be equivalent to the shroud surface and thus the plurality of fluid flow paths would be defined by the impeller hub surface, the housing inner surface and two adjacent blades.
  • Fluid passes through the curved flow paths as illustrated by arrow 7. As the fluid passes through the flow paths the volume along the flow path increases and the fluid is expanded. In the course of this expansion the fluid pressure is reduced by momentum transfer onto blades 6. This energy exchange causes the rotatable assembly to rotate.
  • the shaft is connected to means which uses energy such as compressor or generator. In this way useful work is transferred from turboexpander flow to, for example, compressor operation.
  • the expanded fluid is passed out of turboexpander 15 as illustrated by arrows 1. Typically the fluid is expanded from a pressure within the range of about 300 to 800 psia to a pressure within the range of about 15 to 100 psia.
  • the fluid is passed through the flow passages in a pressure balanced manner wherein the pressure normal to the mean streamline in the meridional plane between the impeller hub surface and the shroud surface is kept substantially constant.
  • One way of maintaining the pressure normal to the mean streamline substantially constant is to provide a turboexpander having flow passage contours which balance the forces on a fluid element including the centrifugal force due to wheel rotation, the centrifugal force due to the curved trajectory of the element, the coriolis force due to the movement in a moving coordinate system and the force due to changes in momentum such that the sum of these forces on a fluid element is about zero as it moves along a pressure balanced flow mean streamline in the meridional plane.
  • a flow path where the forces on a fluid element are balanced as described above is commonly referred to as a pressure balanced flow path.
  • Those skilled in the art of turboexpansion are familiar with the concept of a pressure balanced flow path and the conditions under which pressure balanced flow is attained.
  • a particularly useful and comprehensive text describing turbomachinery in general, and pressure balanced flow paths in particular, is Turbomachines , 0.E. Balje, John Wiley & Sons, New York 1981, particularly chapter 6.
  • the invention comprises the discovery that if high pressure fluid is introduced into the fluid flow paths at a defined negative angle and then passed through the fluid flow paths while maintaining the fluid pressure normal to the mean streamline in the meridional plane substantially constant, an unexpected increase in turboexpander efficiency is attained.
  • FIG. 2 there is shown a simplified diagram of an impeller wheel 20 having blades 21, 22 and 23. Adjacent blades 21 and 22 form the sidewalls of flow path 24 and adjacent blades 22 and 23 form the sidewalls of flow path 25. Assuming impeller wheel 20 rotates in a clockwise direction 26, blade 23 is the leading blade and blade 22 is the trailing blade of flow path or flow channel 25. Similarly blade 22 is the leading blade and blade 21 is the trailing blade of flow path or flow channel 24. The right side of each blade is the leading edge and the left side of each blade is the trailing edge.
  • Elevated pressure fluid is passed into the rotatable assembly at a certain absolute velocity illustrated in Figure 2 by the vector C2.
  • This vector C2 can be resolved as shown in Figure 2 into the vectors W2 and U2.
  • U2 represents the tangential impeller velocity at the point where the fluid enters the rotatable assembly.
  • W2 represents the fluid velocity relative to the impeller surfaces.
  • Vector W2 forms an angle A2 with the line 27 which represents the theoretical extension of blade 22. This angle A2, known as the relative flow angle, represents the angle between the fluid flow and the blades.
  • elevated pressure fluid is introduced into the rotatable assembly of a turboexpander with an absolute velocity such that the angle between the fluid flow and the blades is negative.
  • the elevated pressure fluid flowing into a flow path does so at an angle directed toward the leading edge of the trailing blade of the two adjacent blades forming that flow path.
  • this incidence angle is within the range of from - 10 to - 40 degrees.
  • the desired negative incidence inlet flow is attained by adjusting the inlet nozzles 17 shown in Figure 1. It should be noted that the invention is preferably utilized with substantially no fluid swirl at the outlet of the turbine impeller. This means that the blade exit angle must be such that the fluid exiting into diffuser 1 has essentially zero tangential velocity.
  • Example and Comparative Examples are presented to further illustrate the invention or to demonstrate the improved efficiency attainable by use of the method of this invention. They are not intended to be limiting.
  • Gaseous nitrogen at a pressure of from about 500 to 650 pounds per square inch absolute (psia) was expanded by passage through a turboexpander of this invention to a pressure of from about 70 to 90 psia.
  • the expansion caused the rotatable assembly of the turboexpander to rotate at about 23,000 revolutions per minute (rpm).
  • the fluid passed through each flow path while the pressure normal to the mean streamline in the meridional plane of that flow path was substantially constant and the fluid exited from the impeller with substantially zero swirl.
  • the fluid was passed into the rotatable assembly at an absolute velocity and direction which caused the fluid to have an incidence angle of about -15 degrees.
  • the turboexpander was operated until steady state conditions were reached and the efficiency was measured.
  • the fluid passing into the rotatable assembly is confined in volume by the blade volume.
  • the fluid flow is thus disturbed by this contraction caused by the leading blade thickness. This disturbance results in an efficiency penalty.
  • the fluid is introduced into the rotatable assembly at a negative incidence angle, i.e. directed toward the leading edge of the trailing blade, the fluid flow is divided, the disturbance discussed above is reduced, and the fluid most closely follows the path intended by the designer.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Hydraulic Turbines (AREA)
EP19900113588 1989-07-17 1990-07-16 Turboexpander mit hohem Wirkungsgrad Expired - Lifetime EP0409133B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US38053189A 1989-07-17 1989-07-17
US380531 1989-07-17

Publications (2)

Publication Number Publication Date
EP0409133A1 true EP0409133A1 (de) 1991-01-23
EP0409133B1 EP0409133B1 (de) 1995-01-25

Family

ID=23501533

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19900113588 Expired - Lifetime EP0409133B1 (de) 1989-07-17 1990-07-16 Turboexpander mit hohem Wirkungsgrad

Country Status (4)

Country Link
EP (1) EP0409133B1 (de)
BR (1) BR9003421A (de)
CA (1) CA2021226C (de)
DE (1) DE69016292T2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE40911E1 (en) 1998-04-22 2009-09-08 Cornell Research Foundation, Inc. Canine erythropoietin gene and recombinant protein

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE849038C (de) * 1942-05-23 1952-09-11 Alfred Dr-Ing Buechi Gasturbine
GB838416A (en) * 1955-06-18 1960-06-22 Alfred Johann Buchi Improvements in or relating to turbine impellers
DE2354490A1 (de) * 1972-11-13 1974-05-16 Stal Laval Turbin Ab Gasturbinenaggregat
FR2205927A5 (de) * 1972-11-08 1974-05-31 Bertin & Cie
FR2370875A1 (fr) * 1976-11-13 1978-06-09 Univ Belfast Appareil pour capter l'energie des vagues de la mer et convertisseur d'energie destine a etre utilise dans cet appareil
GB2127905A (en) * 1982-09-30 1984-04-18 Gen Electric Centrifugal compressor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE849038C (de) * 1942-05-23 1952-09-11 Alfred Dr-Ing Buechi Gasturbine
GB838416A (en) * 1955-06-18 1960-06-22 Alfred Johann Buchi Improvements in or relating to turbine impellers
FR2205927A5 (de) * 1972-11-08 1974-05-31 Bertin & Cie
DE2354490A1 (de) * 1972-11-13 1974-05-16 Stal Laval Turbin Ab Gasturbinenaggregat
FR2370875A1 (fr) * 1976-11-13 1978-06-09 Univ Belfast Appareil pour capter l'energie des vagues de la mer et convertisseur d'energie destine a etre utilise dans cet appareil
GB2127905A (en) * 1982-09-30 1984-04-18 Gen Electric Centrifugal compressor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 9, no. 73 (M-368)(1796) 03 April 1985, & JP-A-59 203808 (NISSAN JIDOSHA K.K.) 19 November 1984, *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE40911E1 (en) 1998-04-22 2009-09-08 Cornell Research Foundation, Inc. Canine erythropoietin gene and recombinant protein

Also Published As

Publication number Publication date
CA2021226C (en) 1994-01-11
BR9003421A (pt) 1991-08-27
DE69016292D1 (de) 1995-03-09
EP0409133B1 (de) 1995-01-25
DE69016292T2 (de) 1995-09-07
CA2021226A1 (en) 1991-01-18

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