US2309003A - Cooling arrangement for gas turbines - Google Patents

Cooling arrangement for gas turbines Download PDF

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US2309003A
US2309003A US281555A US28155539A US2309003A US 2309003 A US2309003 A US 2309003A US 281555 A US281555 A US 281555A US 28155539 A US28155539 A US 28155539A US 2309003 A US2309003 A US 2309003A
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Prior art keywords
bucket wheel
wheel
cap
gases
gas turbines
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US281555A
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Rollin H Norris
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General Electric Co
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General Electric Co
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    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to cooling arrangements for gas turbines, particularly of the type of turbines which include a bucket wheel supported on an overhung shaft and having a row of buckets arranged to discharge gases directly into the atmosphere.
  • gas turbines particularly of the type of turbines which include a bucket wheel supported on an overhung shaft and having a row of buckets arranged to discharge gases directly into the atmosphere.
  • Such turbines are often used on aircraft for driving superchargers or generators.
  • the bucket wheel may be subject to excessive heat by the gases discharged therefrom. This is particularly the case where the bucket wheel is mounted so that some of the gases discharged from it are forced towards a central portion thereof by the action of the slip stream.
  • the object of my invention is to provide an improved construction and arrangement of gas turbines whereby such turbines may be operated safetly with gases at high temperatures of the order of 750 C. and above.
  • FIG. 1 illustrates a sectional view of a gas turbine arrangement for aircraft embodying my invention
  • Fig. 2 is a front view of a part of Fig. 1.
  • the arrangement comprises an axial flow gas turbine with a solid bucket wheel I mounted on an overhung shaft ll adjacent a bearing l2 of a supercharger IS.
  • the bucket wheel I has a solid disk with a rim M on which an annular row of buckets I5 is mounted. The outer ends of the buckets are connected by a band I6.
  • An annular nozzle box I1 is mounted adjacent the inlet side of the bucket wheel and has an inlet portion lit for receiving gases from a suitable source, such as the exhaust manifold of a combustion engine, not shown.
  • the nozzle box includes a row of nozzles I9 adjacent the buckets I5 for properly directing operating gas to the bucket wheel.
  • the nozzle box in the present instance is mounted on studs formed on the casing of the supercharger 13 by means including a wall 2
  • which also serves to protect the bearing I2 from heat radiated from the nozzle box ll.
  • direction of discharge into the atmosphere is substantially perpendicular to the direction of the slip stream.
  • the direction of discharge has been indicated in the drawing by an arrow 22 and the direction of the slip stream has been indicated by an arrow 23.
  • the latter in the present instance is parallel to a diameter of the bucket wheel and perpendicular to the direction of discharge of gases, as well as to the axis of rotation of the wheel.
  • the upper portion of the bucket wheel 10 in the drawing is leading and the lower portion of the bucket wheel is trailing. In such arrangement the slip stream forces gases issuing from the leading portion of the bucket wheel towards a central portion thereof and causes excessive temperatures of the wheel.
  • the device comprises a hollow cap 24 coaxially arranged with a bucket wheel and closely spaced with the outer face thereof.
  • the cap has an inner wall 25 and an outer wall 26 with the outer edges of the walls secured together, preferably by fusing to form a space 21.
  • a plurality of radially disposed partitions 28 are secured to the walls inside the space Zlto reinforce the cap. Both walls are essentially concave-shaped when viewed from the bucket wheel.
  • the inner wall 25 has a central portion 30 which is depressed towards the outer wall to engage a central part thereof. This central portion 30 has a plurality of openings 3
  • the diameter of the cap is slightly smaller than the outer diameter of the rim M of the wheel to permit free discharge of gases from the latter.
  • Coolin air under pressure is conducted to the space 21 formed by the cap by means including an annular conduit 33 concentrically spaced from the cap and having an inner diameter slightly larger than the outer diameter of the bucket wheel.
  • This conduit or channel 33 communicates with the cap through three circumferentially spaced the cooling air towards the central portion of the wheel is facilitated by the depressed portion 30 of the inner wall 25 of the cap.
  • the cooling air is discharged from the space 32 between the wheel and the cap through an outer clearance formed between the rim and the cap.
  • the wall portions of the annular conduit 33 and the cap 24 facing each other are both curved to constitute together an annular nozzle with flaring opening through which the gases issuing from the bucket wheel are discharged.
  • Gas turbine arrangement for aircraft comprising a turbine wheel, a nozzle box on one side of the wheel for conducting operating gas thereto and a device for cooling the wheel disposed on the discharge side of the wheel, said the atmosphere.
  • Gas turbine having a bucket wheel, means for conducting operating gas to the inlet side of the wheel, and a cooling and protecting device adjacent the outlet side of the wheel, said device comprising a hollow cap having an inner and an outer wall with edges sealed together, the inner wall having a discharge opening for directing cooling air towards the bucket wheel, an annular conduit concentrically spaced from the cap and having an inlet for cooling medium, and a plurality of circumferentially spaced connecting conduits between the cap and the annular conduit, adjacent walls of the cap and the annular conduit being curved to define a nozzle-shaped space for conducting gases discharged from the bucket wheel.

Description

Jan. 19, 1943. NORRIS.
COOLING ARRANGEMENT FOR GAS TURBINES Filed June 28, 1939 Inventor. Rollin H. Norris,
Attorney Patented Jan. 19, 1943 UNITED STATES PATENT OFFICE Rollin H. Norris, Schenectady, N. Y., assignor to General Electric Company, a corporation of New York Application June 28, 1939, Serial No. 281,555
2 Claims.
The present invention relates to cooling arrangements for gas turbines, particularly of the type of turbines which include a bucket wheel supported on an overhung shaft and having a row of buckets arranged to discharge gases directly into the atmosphere. Such turbines are often used on aircraft for driving superchargers or generators. During operation the bucket wheel may be subject to excessive heat by the gases discharged therefrom. This is particularly the case where the bucket wheel is mounted so that some of the gases discharged from it are forced towards a central portion thereof by the action of the slip stream.
The object of my invention is to provide an improved construction and arrangement of gas turbines whereby such turbines may be operated safetly with gases at high temperatures of the order of 750 C. and above.
For a consideration of what I believe to be novel and my invention, attention is directed to the following description and the claims appended thereto in connection with the accompanying drawing.
In the drawing Fig. 1 illustrates a sectional view of a gas turbine arrangement for aircraft embodying my invention, and Fig. 2 is a front view of a part of Fig. 1.
The arrangement comprises an axial flow gas turbine with a solid bucket wheel I mounted on an overhung shaft ll adjacent a bearing l2 of a supercharger IS. The bucket wheel I has a solid disk with a rim M on which an annular row of buckets I5 is mounted. The outer ends of the buckets are connected by a band I6. An annular nozzle box I1 is mounted adjacent the inlet side of the bucket wheel and has an inlet portion lit for receiving gases from a suitable source, such as the exhaust manifold of a combustion engine, not shown. The nozzle box includes a row of nozzles I9 adjacent the buckets I5 for properly directing operating gas to the bucket wheel. The nozzle box in the present instance is mounted on studs formed on the casing of the supercharger 13 by means including a wall 2| which also serves to protect the bearing I2 from heat radiated from the nozzle box ll. During operation high temperature gases are conducted from the nozzle box to one side of the bucket wheel passing through the passages formed between adjacent buckets and issuing from the other side of the bucket wheel directly into the atmosphere. During operation the bucket wheel may be subject to excessive heat, as pointed out above, especially when the.
direction of discharge into the atmosphere is substantially perpendicular to the direction of the slip stream. The direction of discharge has been indicated in the drawing by an arrow 22 and the direction of the slip stream has been indicated by an arrow 23. The latter in the present instance is parallel to a diameter of the bucket wheel and perpendicular to the direction of discharge of gases, as well as to the axis of rotation of the wheel. With reference to the direction of the slip stream, the upper portion of the bucket wheel 10 in the drawing is leading and the lower portion of the bucket wheel is trailing. In such arrangement the slip stream forces gases issuing from the leading portion of the bucket wheel towards a central portion thereof and causes excessive temperatures of the wheel.
This difiiculty is overcome in accordance with my invention by the provision of a device for protecting and effectively cooling the bucket wheel disk. The device comprises a hollow cap 24 coaxially arranged with a bucket wheel and closely spaced with the outer face thereof. The cap has an inner wall 25 and an outer wall 26 with the outer edges of the walls secured together, preferably by fusing to form a space 21. A plurality of radially disposed partitions 28 are secured to the walls inside the space Zlto reinforce the cap. Both walls are essentially concave-shaped when viewed from the bucket wheel. The inner wall 25 has a central portion 30 which is depressed towards the outer wall to engage a central part thereof. This central portion 30 has a plurality of openings 3| establishing communication between the space 2'! and the space 32 formed between thecap and the outer face of the bucket wheel ID. The diameter of the cap is slightly smaller than the outer diameter of the rim M of the wheel to permit free discharge of gases from the latter. Coolin air under pressure is conducted to the space 21 formed by the cap by means including an annular conduit 33 concentrically spaced from the cap and having an inner diameter slightly larger than the outer diameter of the bucket wheel. This conduit or channel 33 communicates with the cap through three circumferentially spaced the cooling air towards the central portion of the wheel is facilitated by the depressed portion 30 of the inner wall 25 of the cap. The cooling air is discharged from the space 32 between the wheel and the cap through an outer clearance formed between the rim and the cap. The wall portions of the annular conduit 33 and the cap 24 facing each other are both curved to constitute together an annular nozzle with flaring opening through which the gases issuing from the bucket wheel are discharged.
What I claim as new and desire to secure by Letters Patent of the United States is:
1. Gas turbine arrangement for aircraft comprising a turbine wheel, a nozzle box on one side of the wheel for conducting operating gas thereto and a device for cooling the wheel disposed on the discharge side of the wheel, said the atmosphere.
2. Gas turbine having a bucket wheel, means for conducting operating gas to the inlet side of the wheel, and a cooling and protecting device adjacent the outlet side of the wheel, said device comprising a hollow cap having an inner and an outer wall with edges sealed together, the inner wall having a discharge opening for directing cooling air towards the bucket wheel, an annular conduit concentrically spaced from the cap and having an inlet for cooling medium, and a plurality of circumferentially spaced connecting conduits between the cap and the annular conduit, adjacent walls of the cap and the annular conduit being curved to define a nozzle-shaped space for conducting gases discharged from the bucket wheel.
ROLLIN H. NORRIS.
US281555A 1939-06-28 1939-06-28 Cooling arrangement for gas turbines Expired - Lifetime US2309003A (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2429936A (en) * 1943-12-18 1947-10-28 Allis Chalmers Mfg Co Turbine mounting
US2635419A (en) * 1948-09-30 1953-04-21 Curtiss Wright Corp Adjustable discharge nozzle for jet engines
US2743579A (en) * 1950-11-02 1956-05-01 Gen Motors Corp Gas turbine engine with turbine nozzle cooled by combustion chamber jacket air

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2429936A (en) * 1943-12-18 1947-10-28 Allis Chalmers Mfg Co Turbine mounting
US2635419A (en) * 1948-09-30 1953-04-21 Curtiss Wright Corp Adjustable discharge nozzle for jet engines
US2743579A (en) * 1950-11-02 1956-05-01 Gen Motors Corp Gas turbine engine with turbine nozzle cooled by combustion chamber jacket air

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