US2445661A - Axial flow turbine, compressor and the like - Google Patents

Axial flow turbine, compressor and the like Download PDF

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Publication number
US2445661A
US2445661A US518180A US51818044A US2445661A US 2445661 A US2445661 A US 2445661A US 518180 A US518180 A US 518180A US 51818044 A US51818044 A US 51818044A US 2445661 A US2445661 A US 2445661A
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turbine
fixed
casing
compressor
hand
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US518180A
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Constant Hayne
Merchant Wilfred
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Metropolitan Vickers Electrical Co Ltd
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Metropolitan Vickers Electrical Co Ltd
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • AXIAL FLOW TURBINES COMPRESSORS AND THE LIKE Filed Jan. 15, 1944 v INVEN f-S m h dd W iputcnted July 20, 1948 UNITED STATES PATENT OFF! AXIAL FLOW TURBINE, COMPRESSOR AND THE LIKE Application January 13, 1944, Serial No. 518,180 In Great Britain September 22, 1941 Section 1, Public Law 690, August 8, 1946 Patent expires September 22, 1961 8 Claims.
  • This invention relates to turbines and other axial flow machines such as rotary compressors wherein the blading is subjected to fluid at relatively high temperatures as in internal combustion turbine plant.
  • the invention specifically relates to the mechanical connecting means between the outer casing and the fixed blade carrying members associated therewith on the one hand and the coaxial inner fixed member carrying the rotor bearing on the otherhand. In operation the temperatures assumed by these two prtions respectively difief' considerably.
  • the attachment of the casing of the turbine orthe like to the inner fixed member of the turbine or compressor, which member may be the periphery of a flexible mechanical support is through the intermediary of some or all of the fixed blades, prefably of the first stage of the turbine, which blades at their inner ends or foundation rings" at these ends are provided with radial pegs or pins, preferably integrally, which engage in radial holes in the inner fixed member aforesaid.
  • these pegs or pins are of barrel shape and fit snugly into cylindrical radial holes.
  • the arrangement according to the invention is more'particularly but not exclusively applicable to turbines or the like where the rotor is overhung from its bearing.
  • the first blade stage end of the turbine casing may be directly connected to the delivery end of an annular combustion chamber, to the remote end of which in axial alignment is connected the compressor which is driven by direct coupling through an internal shaft from the turbine, the casing of the internal combustion chamber being supported at one end by the casing of the turbine and at the other end from the casing of the compressor.
  • the turbine casing consists of a simple cylindrical outer wall with an end flange to which is secured such as by set screws one end of an inner casing wall carrying the fixed blading, and the outlet or annular delivery duct from the turbine, whilst the other end of the inner casing has secured to it ternate rings in segmental form being foundation rings carrying the fixed blading of the turbine. It will be appreciated that with this orrangement further flexlbllity in the interests of thermal expansion in the radial direction for the outer casing is provided.
  • a space for cooling fluid isv preferably provided between said inner and outer casing walls.
  • the rotor of the turbine in question is shown as having an integral stub shaft 2 splined to a sleeve 3 with a flange 8a having a plurality of peripheral perforations 4 for bolting to the main shaft (not shown) extending along the axis 5 through the combustion chamber, part of which is generally indicated at 6, to the air compressor (not shown) supplying said combustion chamber, which is of annular form and, as aforesaid, directly connects the exhaust of the compressor with the annular inlet member 1 of the turbine which-hastthe annular exhaust or delivery passage formed by the tubes 8 and 8.
  • the casing, generally. indicated at ll), of the turbine is connected at the right-hand end with the combustion chamber 6 and is connected at the left-hand end with the gas delivery members 8 and 8.
  • the illustrated member l5 may be one of a relatively small number of radial supporting members uniting the tubular members 8a and 8a to which the members 8 and 8 are welded.
  • the turbine casing Hi is mechanically connected through at least some of the blading l3 in the first row, through the flexible dished member l1, with the stationary internal member IS.
  • the latter carries the fixed race l8 of the turbine rotor bearing H! which is shown as, and preferably is, of the ball type, the inner race 20 of which is carried on the sleeve 3 of the turbine rotor.
  • the bearing housing is comprised peripherally by the inner cylindrical surface of the fixed tubular member i6, at the right-hand end by an internal flange 2
  • and 22 have cylindrical flanges 24 and 25, between the inner surfaces of which and the shaft 2 gas-tight packing of per se well known form may be provided: and arrangements will be made for lubricating and cooling the bearing I9, which arrangements per se form no part of the present invention.
  • the inner flange of the dish member I1 is bolted at 26 to an external flange 21 on the internal stationary member iii.
  • the fixed blading l3 of the first row is provided with an inner foundation ring 28 which has radial pegs or pins 29 according to the main feature of the present invention, which pegs 29 engage in radial holes 30 in the outer peripheral portion of the dished member I1.
  • the pegs 29 may be provided with helical or other grooves 3
  • the turbine casing l comprises on the one hand the simple cylindrical outer wall 32 (which is a continuation of the combustion chamber outer casing) and the inner wall, hereinafter described, on the other hand.
  • the annular combustion chamber 6 has the outer wall 33 providing, with casing 32, the outer jacket space 34, and has the inner wall 35 providing, with an innermost wall 36, the inner jacket space 3611. Relatively cool air flows in the jacket spaces 34 and 36a as indicated by the arrows.
  • the lefthand end of the jacket space 34 is divided by an annular partition 31 for directing a good flow of air into the annular space between the inner and outer walls of the turbine casing.
  • the tubular exhaust member 8a has secured to its flange 38 on the right-hand side a flanged blade-spacing and gas-guide member 39, and on the left-hand side a member 43 receiving the left-hand end of the extension of the casing 32.
  • a flanged blade-spacing and gas-guide member 39 Between the right-hand flange of the member 39 and another double-flanged blade-spacing and gas-guide member 4
  • the foundation ring 44 of the first row I3 of fixed blading is similarly clamped between the right-hand flange of the member 4
  • annular space is provided between the inner wall comprised by the built-up members 39 to 44 and member 1, on the one hand, and the cylindrical outer casing wall 32, on the other hand, to the right-hand end of which space cooling air can be delivered from the jacket space 34 of the combustion chamber 6.
  • the annular member 39 is provided with ducts 45 through which the cooling air can pass into the delivery passage 8. 9 of the turbine. Circulation of the cool air (or gases) through the aforesaid annular space is maintained by the pressure drop from the inlet of the turbine to its exhaust, and it will be appreciated that no sealed joint need therefore be made between the annular passage 34 of thecombustion chamber and the annular passage around the turbine.
  • Anaxial fiow machine the blading of which is subjected to fluid at relatively high temperature comprising an outer casing of the machine and fixed blade-carrying members associated therewith, a fixed member in the interior of the machine, a ring connecting the inner ends of at least one row of the fixed blades of the machine, and a mechanical connection between said ring and fixed member comprising radial pins on the inner periphery of said ring, engaging in radial holes in said inner fixed member.
  • a machine as claimed in claim 1, wherein said fixed member comprises a flexible member of substantially dished shape.
  • a machine as claimed in claim 1 wherein a clearance is provided between said ring and fixed member for fiow of cooling air therethrough.
  • An internal combustion turbine plant comprising an outer casing, an inner wall carrying axially spaced rows of fixed blading, an annular delivery duct, means connecting said outer casing REFERENCES CITED

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

July 20, 1948. H. CONS'MTANT ETAL 2,445,661
AXIAL FLOW TURBINES, COMPRESSORS AND THE LIKE Filed Jan. 15, 1944 v INVEN f-S m h dd W iputcnted July 20, 1948 UNITED STATES PATENT OFF! AXIAL FLOW TURBINE, COMPRESSOR AND THE LIKE Application January 13, 1944, Serial No. 518,180 In Great Britain September 22, 1941 Section 1, Public Law 690, August 8, 1946 Patent expires September 22, 1961 8 Claims.
This invention relates to turbines and other axial flow machines such as rotary compressors wherein the blading is subjected to fluid at relatively high temperatures as in internal combustion turbine plant. v The invention specifically relates to the mechanical connecting means between the outer casing and the fixed blade carrying members associated therewith on the one hand and the coaxial inner fixed member carrying the rotor bearing on the otherhand. In operation the temperatures assumed by these two prtions respectively difief' considerably.
According to the present invention in order to take care of the differential expansion due to the temperature diiferences above indicated the attachment of the casing of the turbine orthe like to the inner fixed member of the turbine or compressor, which member may be the periphery of a flexible mechanical support, is through the intermediary of some or all of the fixed blades, prefably of the first stage of the turbine, which blades at their inner ends or foundation rings" at these ends are provided with radial pegs or pins, preferably integrally, which engage in radial holes in the inner fixed member aforesaid. Preferably these pegs or pins are of barrel shape and fit snugly into cylindrical radial holes. With this arrangement freedom for radial expansion is permitted between the casing and fixed blades carried thereby on the one hand, and the inner fixed member on the other hand, whilst the casing is rigidly located relatively to the inner fixed member in all directions other than that required for such radial expansion.
The arrangement according to the invention is more'particularly but not exclusively applicable to turbines or the like where the rotor is overhung from its bearing. It will be appreciated that the first blade stage end of the turbine casing may be directly connected to the delivery end of an annular combustion chamber, to the remote end of which in axial alignment is connected the compressor which is driven by direct coupling through an internal shaft from the turbine, the casing of the internal combustion chamber being supported at one end by the casing of the turbine and at the other end from the casing of the compressor.
In a convenient arrangement according to a subsidiary feature of the invention the turbine casing consists of a simple cylindrical outer wall with an end flange to which is secured such as by set screws one end of an inner casing wall carrying the fixed blading, and the outlet or annular delivery duct from the turbine, whilst the other end of the inner casing has secured to it ternate rings in segmental form being foundation rings carrying the fixed blading of the turbine. It will be appreciated that with this orrangement further flexlbllity in the interests of thermal expansion in the radial direction for the outer casing is provided. A space for cooling fluid isv preferably provided between said inner and outer casing walls.
The single figure or the accompanying drawing is a, half sectional elevation of part of an internal combustion turbine plant embodying the features of the present invention.
Referring to the drawing, at I is shown the rotor of the turbine in question. This rotor is shown as having an integral stub shaft 2 splined to a sleeve 3 with a flange 8a having a plurality of peripheral perforations 4 for bolting to the main shaft (not shown) extending along the axis 5 through the combustion chamber, part of which is generally indicated at 6, to the air compressor (not shown) supplying said combustion chamber, which is of annular form and, as aforesaid, directly connects the exhaust of the compressor with the annular inlet member 1 of the turbine which-hastthe annular exhaust or delivery passage formed by the tubes 8 and 8. The casing, generally. indicated at ll), of the turbine is connected at the right-hand end with the combustion chamber 6 and is connected at the left-hand end with the gas delivery members 8 and 8. The
- turbine rotor I carries two rows of blading indicated at H and I2, whilst the turbine casing carries two fixed stages of blading indicated at I3 and I4, whilst there may be fixed guide blading l5 at the delivery end: alternatively the illustrated member l5 may be one of a relatively small number of radial supporting members uniting the tubular members 8a and 8a to which the members 8 and 8 are welded.
As hereinbefore indicated the turbine casing l8 and fixed blading I3, I l are connected with, and
in fact may be carried by, an internal structure of the plant which is shown as an example as the tubular member I6 extending through the combustion chamber 6 at least to the air delivery end of the compressor, this arrangement, however, per se forming no part of the present invention. The turbine casing Hi, the structure or which is hereinafter described in more detail, is mechanically connected through at least some of the blading l3 in the first row, through the flexible dished member l1, with the stationary internal member IS. The latter carries the fixed race l8 of the turbine rotor bearing H! which is shown as, and preferably is, of the ball type, the inner race 20 of which is carried on the sleeve 3 of the turbine rotor. The bearing housing is comprised peripherally by the inner cylindrical surface of the fixed tubular member i6, at the right-hand end by an internal flange 2| fixed on, or may be integral with, the member l6, and at the left-hand end by a washer-shaped member 22 bolted at 23 to the left-hand end of the member IS. The members 2| and 22 have cylindrical flanges 24 and 25, between the inner surfaces of which and the shaft 2 gas-tight packing of per se well known form may be provided: and arrangements will be made for lubricating and cooling the bearing I9, which arrangements per se form no part of the present invention. The inner flange of the dish member I1 is bolted at 26 to an external flange 21 on the internal stationary member iii.
The fixed blading l3 of the first row is provided with an inner foundation ring 28 which has radial pegs or pins 29 according to the main feature of the present invention, which pegs 29 engage in radial holes 30 in the outer peripheral portion of the dished member I1. The pegs 29 may be provided with helical or other grooves 3| for the reception of cooling air from the jacket of the combustion chamber. It will be noticed that there is a slight but appreciable clearance between the outer periphery of the dished member l1 and the inner periphery of the foundation ring 28.
The turbine casing l comprises on the one hand the simple cylindrical outer wall 32 (which is a continuation of the combustion chamber outer casing) and the inner wall, hereinafter described, on the other hand. The annular combustion chamber 6 has the outer wall 33 providing, with casing 32, the outer jacket space 34, and has the inner wall 35 providing, with an innermost wall 36, the inner jacket space 3611. Relatively cool air flows in the jacket spaces 34 and 36a as indicated by the arrows. The lefthand end of the jacket space 34 is divided by an annular partition 31 for directing a good flow of air into the annular space between the inner and outer walls of the turbine casing.
The tubular exhaust member 8a has secured to its flange 38 on the right-hand side a flanged blade-spacing and gas-guide member 39, and on the left-hand side a member 43 receiving the left-hand end of the extension of the casing 32. Between the right-hand flange of the member 39 and another double-flanged blade-spacing and gas-guide member 4| is secured by bolts 42 the foundation ring 43 carrying the second row of fixed turbine blading M. The foundation ring 44 of the first row I3 of fixed blading is similarly clamped between the right-hand flange of the member 4| and the flange of the annular inlet member 1, into which the left-hand ends of the walls 33 and 35 of the combustion chamber extend.
It will be appreciated that an annular space is provided between the inner wall comprised by the built-up members 39 to 44 and member 1, on the one hand, and the cylindrical outer casing wall 32, on the other hand, to the right-hand end of which space cooling air can be delivered from the jacket space 34 of the combustion chamber 6. The annular member 39 is provided with ducts 45 through which the cooling air can pass into the delivery passage 8. 9 of the turbine. Circulation of the cool air (or gases) through the aforesaid annular space is maintained by the pressure drop from the inlet of the turbine to its exhaust, and it will be appreciated that no sealed joint need therefore be made between the annular passage 34 of thecombustion chamber and the annular passage around the turbine.
We claim:
1. Anaxial fiow machine the blading of which is subjected to fluid at relatively high temperature comprising an outer casing of the machine and fixed blade-carrying members associated therewith, a fixed member in the interior of the machine, a ring connecting the inner ends of at least one row of the fixed blades of the machine, and a mechanical connection between said ring and fixed member comprising radial pins on the inner periphery of said ring, engaging in radial holes in said inner fixed member.
2. A machine as claimed in claim 1, wherein I said pegs or pins are of barrel shape and fit snugly into radial cylindrical holes in the inner fixed member.
3. A machine as claimed in claim 1, wherein said fixed member comprises a flexible member of substantially dished shape.
4. A machine as claimed in claim 1, wherein said fixed member extends outwardly toward said ring, and said machine including a blade carrying rotor, and a bearing interposed between said rotor and the inner portion of said fixed member.
5. A machine as claimed in claim 1, wherein a clearance is provided between said ring and fixed member for fiow of cooling air therethrough.
6. A machine as claimed in claim 1, wherein said pins are grooved for reception of cooling air, and a clearance is provided between said ring and fixed member for supplying cooling air to the grooves in said pins.
'7. A machine as claimed in claim. 1, wherein a clearance is provided between said ring and fixed member for fiow of cooling air therethrough, and including a combustion chamber having walls for directing cooling air to said clearance.
8. An internal combustion turbine plant, comprising an outer casing, an inner wall carrying axially spaced rows of fixed blading, an annular delivery duct, means connecting said outer casing REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS t'aimber Name Date 1,331,766 Hemingway Feb. 24, 1920 1,346,509 olhovsky July 13, 1920 2,080,425 Lysholm May 18, 1937v 2282,894 Sheldon May 12, 1942 2,326,072 Seippel Aug. 3, 1943
US518180A 1941-09-22 1944-01-13 Axial flow turbine, compressor and the like Expired - Lifetime US2445661A (en)

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GB12272/41A GB589541A (en) 1941-09-22 1941-09-22 Improvements in axial flow turbines, compressors and the like

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US2557898A (en) * 1947-11-03 1951-06-19 Albert S Thompson Gas turbine diaphragm
US2584899A (en) * 1945-01-23 1952-02-05 Power Jets Res & Dev Ltd Construction of stator elements of turbines, compressors, or like machines
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US2622843A (en) * 1947-12-17 1952-12-23 Packard Motor Car Co Turbine construction for turbojet engines
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