US3740168A

US3740168A - Tubular encased turbo-machine with axially spaced sealing rings for compartmentizing the compressor and turbine components

Info

Publication number: US3740168A
Application number: US00198383A
Authority: US
Inventors: H Hug; M Zimmermann; P Moser; H Schwarz
Original assignee: BBC Brown Boveri France SA
Current assignee: BBC Brown Boveri AG Switzerland; BBC Brown Boveri France SA
Priority date: 1970-11-18
Filing date: 1971-11-12
Publication date: 1973-06-19
Anticipated expiration: 1990-06-19
Also published as: GB1340755A; CH524087A; DE2060496A1; FR2114679A5

Abstract

A tubular encased turbo-machine structure comprises a tubular concrete reinforced casing in which a turbo-machine group is inserted subsequent to its assembly. The various machines of the group such as the compressors and turbine are compartmentized within the casing by means of radially displaceable segmented sealing rings located within the casing, these rings being initially in a retracted state with their inner peripheries essentially flush with the inner surface of the casing to facilitate installation of the assembled turbo-machine group in the casing, and the rings thereafter being displaced radially inward so as to establish a sealing contact with the peripheries of the guide blade carrier components of the several machines and thus compartmentize the interior of the tube so that the several machines of the group are separated each from the other.

Description

United States Patent [1 1 Hug et al.

[ TUBULAR ENCASED TURBO-MACHINE WITH AXIALLY SPACED SEALING RINGS FOR COMPARTMENTIZING THE COMPRESSOR AND TURBINE COMPONENTS [75] Inventors: Hermann Hug, Klingnau; Paul Moser, Dietlikon; Hans Schwarz, Nussbaumen; Max Zimmermann, Untersiggenthal, all of Switzerland [73] Assignee: Aktiengesellschaft Brown, Boveri &

Cie, Baden, Switzerland 22 Filed: Nov. 12,1971

21 Appl.No.: 198,383

['30] Foreign Application Priority Data Nov. 18, 1970 Switzerland 17155/70 [52] US. Cl. 417/360, 415/126, 415/135,

415/219 [51] Int. Cl. F04b 17/00 [58] Field of Search 417/307, 360;

[56] References Cited UNITED STATES PATENTS 3,269,677 8/1966 Stoeckly 415/126 3,658,438 4/1972 Coleman et al 415/219 R Primary Examiner -C. J. Husar Attorney RaIph E Parker and Eug ene j. RkiBitE [5 7 ABSTRACT A tubular encased turbo-machine structure comprises a tubular concrete reinforced casing in which a turbomachine group is inserted subsequent to its assembly. The various machines of the group such as the compressors and turbine are compartmentized within the casing by means of radially displaceable segmented sealing rings located within the casing, these rings being initially in a retracted state with their inner peripheries essentially flush with the inner surface of the casing to facilitate installation of the assembled turbo-machine group in the casing, and the rings thereafter being displaced radially inward so as to establish a sealing contact with the peripheries of the guide blade carrier components of the several machines and thus compartmentize the interior of the tube so that the several machines of the group are separated] each from the other.

6 Claims, 4 Drawing Figures Patented June 19, 1973 2 Sheets-Sheet l N m f m A Q9 BE m a Q s s Patented June 19, 1973 3,740,168

2 Sheets-Sheet 2 FIGS, v FIG-4 TUBULAR ENCASED TURBO-MACHINE WITH AXIALLY SPACED SEALING RINGS FOR COMPARTMENTIZING THE COMPRESSOR AND TURBINE COMPONENTS The present invention relates to gaseous fluid operated machines such as turbo-machine groups or the like which are encased in a concrete reinforced tube, and more particularly to an improved constructional arrangement of the machine group within the tube which provides a novel arrangement of axially spaced sealing rings within the tube that establishes separate compartments for respectively receiving the turbine and various stages of the compressor.

Tubular encased turbo-machine groups are already known in the art and with respect to these, the supply of the operating fluid to the various stages of the compressor and to the turbine has been effected by means of separate supply ducts which enter through the wall of the tube and connect to the inlet ends of the compressors and turbine. However, because of different heat expansion characteristics as between the concrete-encased tubes and the turbo-machine components, the connections of the supply ducts to the different pressure stages result in considerably high reaction forces which can be compensated out only by highly elaborate measures, such as axially moving bellows. A further disadvantage is that extra space is required, since the supply duct connections must be made available for assembly and disassembly and inspection.

For these reasons, the use of reinforced tube encased turbo-machines has not heretofore been as successful as hoped, for although the tubular casing structure has been simplified, extensive work has been necessary in order to assemble the machines within the casing.

A principal object of the present invention is to provide an improved structural arrangement whereby the prior disadvantages are obviated and in particular ensure that any tube reaction forces have no adverse affects upon the guide blade carriers of the compressor stages and turbine and other fittings which are provided within the encasing tube.

In accordance with the invention, the tubular casing within which the turbo-machine group is placed, is divided into axially separated compartments individual to the various compressor stages and turbine, and these compartments are established by means of axially spaced sealing rings carried by the tubular casing and which are displaced in a radially inward direction after the turbo-machine has been completely assembled and thereafter inserted in the casing so as to sealingly engage at their inner peripheries the surface of the correspondingly positioned guide blade carriers of the compressors and turbine. Preferably each sealing ring is divided radially into a plurality of segments which are movable radially inwards or outwards. The radial joints between adjacent ring segments can also be provided with sealing lips. This radial displacement of the ring segments permits the rings to be initially shifted radially outward so that their inner peripheries are essentially flush with the inner surface of the tubular casing, thus simplifying insertion of a completely assembled turbomachine group into the casing, after which the ring segments are then moved radially inward to engage the peripheries of the guide blade carriers of the compressor and turbine and complete the sealing between the various operating sections of the machine group. Moreover, due to the fact that the sealing rings establish individually sealed-off compartments for the compressor and turbine components, the various ducts for supplying and removing the pressurized fluid medium to and from the compressor stages and turbine can be and are terminated at the corresponding pass-through points in the wall of the casing and hence are not rigidly connected to the fluid inlets and outlets of the compressors and turbine thus eliminating the possibility of creating any undesirable reaction forces at the machine. A further advantage of the improved construction, in addition to the previously mentioned simplification in assembly and dis-assembly of the turbo-machine group with respect to its enclosing casing is that there is also considerable savings in the overall space requirements for the installation.

The foregoing as well as other objects and advantages inherent in the improved construction will become more apparent from the following detailed description of a preferred embodiment thereof and the accompanying drawings wherein:

FIG. 1 is a view in longitudinal central section of a turbo-machine group encased within a concrete reinforced tube, the machine group consisting of several axial flow compressor stages and a turbine stage and wherein radially displaceable sealing rings in accordance with the invention serve to compartmentize the interior of the tube into separate sections each receiving one of the compressor stages and the turbine.

FIG. 2 is an end view of one of the radially displaceable sealing ring structures;

FIG. 3 is a cross-sectional view of that part of the sealing ring structure denoted within the circle legended A in FIG. 2; and

FIG. 4 is a sectional view taken on line B--B of FIG. 3.

With reference now to the drawings, and to FIG. 1 in particular, the tube for enclosing the turbo-machine group is indicated at 1 and the concrete reinforcing sur' rounding the tube is indicated at 15.

The turbo-machine group within tube 1 is seen to be comprised of several axial

flow compressor stages

4, 5 and 6 connected in cascade and a turbine 3, the bladed rotors of all four of which are mounted on a common shaft 2. The cylindrical stator components of all four machines which carry the guide blading are indicated at 7 and, in accordance with the invention, radially displaceable sealing rings 8 are provided interiorly of casing 1 in axially spaced relation and these, when moved into sealing engagement with the peripheries of the stator components, i.e., the guide blade carriers 7, serve to compartmentize the interior of the tube 1 into separate sections each receiving one of the compressor stages and the turbine respectively, and its fluid inlet and outlet. The sealing rings 8 are supported in circular grooves 14 provided in ring-shaped members 13, the grooves 14 being open in the radially inward direction so as to permit the required radial displacement of the sealing rings inwardly to engage the peripheries of the guide blade carriers 7. The radially inward positions of the sealing rings 8 are depicted in FIG. 1 and hence it will be self-evident that these establish a sealed compartment within the tube 1 for compressor stage 4 together with its fluid inlet 9a and outlet 10a; similarly, other sealed compartments are established by others of the sealing rings 8 for compressor stage 5 together with its fluid inlet 9b and outlet 10b, as well as for compressor stage 6 together with its fluid inlet 96 and outlet 10c and for turbine 3 together with its fluid inlet 11 and outlet 12.

It will be seen that the fluid inlet and outlet ducts 9a9c and l0a-l0c for the compressor stages 4-6 are likewise encased in the concrete 15, and heat insulation liners 17 are provided for the fluid inlet and outlet ducts ll, 12 for turbine 3 in order to protect the concrete from the heat content of the hot combustion gases which flow through the turbine. Since the turbine guide blade carrier 7' likewise is subjected to high temperatures, its interior surface is likewise provided with an insulating liner 16.

Heat removal and protection against heat can be enhanced by the provision of by-passes, in which event, passages (not shown) extend from the outlet of the highest pressure compressor stage 6 into an annular chamber 33 provided between the outer surface of the guide blade carrier 7 and the encasing tube 1; relatively cool air from compressor stage 6 thus discharges into annular chamber 33 and, having taken up some heat from the turbine structure, discharges through the turbine exhaust outlet 12. Tubes through which a coolant is passed can also be embedded in the concrete 15 as a measure for removing heat from the tube 1.

The tube 1 is closed at the turbine end by means of a closure plate 34 which is secured to the left end of the guide blade carrier 7 and which is maintained in place by means of a ring 35 which is anchored in the wall of the tube 1. At the opposite end of tube 1 the end 36 of shaft 2 passes through a lock opening 37 to a coupling which connects this shaft to the shaft of a generator, not shown, which constitutes the load for the turbomachine group.

The structural details of each of the sealing rings 8 depicted only in a general manner in FIG. 1 are shown in FIGS. 2 to 4. FIG. 2 depicts the sealing ring 8 in the radially inward position, i.e., in contact at its inner periphery with the cylindrical surface of a guide blade carrier 7. As shown in this view, ring 8 is subdivided circumferentially into six ring segments 19 and the planes of the joints 20 between the adjoining ends of adjacent segments extend in a radial direction. However, this specific construction can be departed from if movement of the ring segments in accordance with a change in ring diameter is allowed for.

In order to transmit radial displacement to the six ring segments 19 in groove 14 the adjoining ends thereof are formed with grooves 26 in which coupling projections 21 engage. Secured to each coupling projection 26 is a piston rod 22 connected to piston 23 which operates in a cylinder 24 secured partially with the body of the grooved ring member 13 and which also extends radially outward from the latter into a void in the concrete 15 developed by a cylindrical casing 25 secured to the outer periphery of the ring member 13. The coupling members 21 are constructed so as not only to provide at least some compensation for manufacturing inequalities but also to transmit a uniform pressure to the ring segments 19.

If further sealing of the radial joint planes, other than that established by contact between the end faces of the segments 19, is held to be desirable, a sealing lip, not illustrated, can be provided at these joint planes, in a simple manner.

FIGS. 3 and 4 show at an enlarged scale, the structure within the area of FIG. 2 denoted by circle A."

These views show the adjoining end portions of

adjacent ring segments

19, 19a, the grooves 26, coupling member 21, piston rod 22, piston 23, cylinder 24 and cylinder housing 25. Also depicted in these two views are the particulars of the construction of the circular groove 14 in which the ring segments 19 operate in a radial direction, an O-ring 29 in the wall of the groove 14 to provide sealing in the radial direction, and spacers 30 which serve to locate the ring segments 19 in their proper axial position within groove 14.

At the inner periphery of each ring segment 19, a sealing strip 28 is provided which ensures a gas-tight seal between the ring segments 19 of the sealing rings 8 and the circumferential surface of the guide blade carriers 7. These sealing strips 28 are secured in place on their respective ring segments 19 by means of a clamping segment 27.

Hydraulic lines

31 and 32, shown in FIG. 4 serve to supply hydraulic fluid selectively to cylinders 24 on opposite sides of their piston 23 so that the pistons and hence the ring segments 19 can be actuated in a radially inward direction to effect the desired sealing engagement of the rings 8 with the surface of the guide blade carriers 7, or to retract the ring segments 19 to a position substantially flush with the inner surface of the casing 1 so as to enable the assembled turbomachine to be easily installed in casing l or removed therefrom.

The sealing strips 28 are preferably made from elastomers or plastics if the temperatures of the working gaseous medium are relatively low. However, metal or heat-resistant fabrics can readily and fairly cheaply be utilized for these sealing strips in cases wherein the turbo-machine is of the combustion type wherein the gas temperatures are rather high.

We claim:

1. A turbular encased turbo-machine structure comprising a tubular casing, a turbo-machine group comprising a plurality of axially spaced and shaft-coupled turbo-machine units such as compressors and turbines operating at different pressures and which are inserted as an assembly in said tubular casing, each said turbomachine unit including a guide blade carrier and an associated gaseous fluid inlet and outlet, and a plurality of sealing rings interposed respectively between the outer cylindrical peripheral surfaces of the guide blade carriers and the inner surface of said tubular casing to establish individually sealed compartments within said casing for each of said turbo-machine units, each of said sealing rings being radially divided into a plurality of ring segments, and means for actuating said ring segments in a radially inward direction to engage and effect a sealing engagement with the periphery of the guide blade carrier associated therewith, and also in a radially outward direction to a disengaged position enabling said turbo-machine group to be inserted in or removed from said tubular casing.

2. A turbular encased turbo-machine structure as defined in claim 1 wherein the gaseous fluid ducts for conveying the fluid to and from said inlet and outlets of each turbo-machine unit terminate inside the tubular casing within the respective sealed compartment, and each said inlet and outlet is disposed between two axially spaced sealing rings.

3. A tubular encased turbo-machine structure as defined in claim 1 wherein the end faces of the ring segments of each sealing ring are in contact with each other and include sealing lips therebetween.

4. A tubular encased turbo-machine structure as defined in claim 1 wherein said means for actuating the segments of each of said sealing rings is constituted by hydraulic motors the pistons of which are connected to said ring segments.

5. A tubular encased turbo-machine structure as defined in claim 4 wherein the piston of each hydraulic motor is connected to the ring segments by means of a coupling member actuated by the piston, each said coupling member being constituted by a projection extending from the piston rod into grooves provided respectively in the end faces of adjoining ring segments.

6. A tubular encased turbo-machine structure as desupporting member also functions as a support for said hydraulic motors.

Claims

1. A turbular encased turbo-machine structure comprising a tubular casing, a turbo-machine group comprising a plurality of axially spaced and shaft-coupled turbo-machine units such as compressors and turbines operating at different pressures and which are inserted as an assembly in said tubular casing, each said turbo-machine unit including a guide blade carrier and an associated gaseous fluid inlet and outlet, and a plurality of sealing rings interposed respectively between the outer cylindrical peripheral surfaces of the guide blade carriers and the inner surface of said tubular casing to establish individually sealed compartments within said casing for each of said turbo-machine units, each of said sealing rings being radially divided into a plurality of ring segments, and means for actuating said ring segments in a radially inward direction to engage and effect a sealing engagement with the periphery of the guide blade carrier associated therewith, and also in a radially outward direction to a disengaged position enabling said turbomachine group to be inserted in or removed from said tubular casing.

6. A tubular encased turbo-machine structure as defined in claim 4 and which furtHer includes a ring member structurally integrated in the wall of said tubular casing for supporting each of said sealing rings, the segments of each said ring being received in a groove provided in said ring supporting member, and said ring supporting member also functions as a support for said hydraulic motors.