US2863634A - Shroud ring construction for turbines and compressors - Google Patents

Shroud ring construction for turbines and compressors Download PDF

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US2863634A
US2863634A US551583A US55158355A US2863634A US 2863634 A US2863634 A US 2863634A US 551583 A US551583 A US 551583A US 55158355 A US55158355 A US 55158355A US 2863634 A US2863634 A US 2863634A
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section
shroud ring
casing
ring
arcuate
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US551583A
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Chamberlin Reginald He Douglas
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Napier Turbochargers Ltd
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D Napier and Son Ltd
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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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • This invention relates to a construction of shroud ring for turbines or compressors, that is to say the shroud ring which closely surrounds a ring of rotor blades in a turbine or compressor.
  • a shroud ring assembly comprises a tubular outer casting, and an annular shroud ring disposed within the outer casing and comprising a series of separate arcuate circumferentiallyextending sections each of which is rigidly connected at one end only (hereinafter called the fixed end) to the tubular outer casing and is supported at its other end (hereinafter called the free end) from the fixed end of the adjacent arcuate section through a connection which allows limited free relative circumferential movement between the adjacent ends of the two arcuate sections but substantially prevents relative radial movement between such adjacent ends.
  • connection between the fixed end of each arcuate section and the free end of an adjacent arcuate section is in the form of a step on the end face of one of the sections engaging a coopcrating step on the adjacent end face of the other section, it being understood that the step is arranged so that the free end of the appropriate section is held from inward radial movement relatively to the fixed end of the other section by the inter-engaging steps.
  • a key may be provided extending between and engaging axially extending slots in the adjacent ends of the two sections.
  • each arcuate section of the shroud ring is preferably of such cross section as to provide Within it a chamber having means by which cooling air can be supplied to and permitted to escape from it.
  • one or more sheet metal baflle members are then preferably provided within each arcuate section and arranged to define with the inner circumferential wall at least of the arcuate section a narrow passage through which the cooling air is caused by the baflle member to fioW.
  • each arcuate section is secured to the tubular outer casing by means of a radially arranged bolt, stud, or the like engaging a bore in the appropriate end of the arcuate section.
  • each of the bores in question may be screwthreaded and be engaged by the inner screwthreaded end of a bolt passing freely through a radial hole in the tubular outer casing.
  • each arcuate section of the shroud ring is of channelshaped cross-section in planes containing the axis of the tubular casing, and one construction embodying arcuate sections of this form and a modification thereof, are shown in the accompanying drawings, in which:
  • Figure 1 is a sectional view in a plane containing the axis of a combustion turbine of the part of such turbine including a shroud ring according to the invention and two adjacent rings of stator blades, the parts shown in the drawing being for convenience limited substantially to those necessary for an understanding of the invention itself and not representing a complete cross-section through the turbine,
  • Figure 2 is a cross-section on the line 22 of Figure 1 through the shroud ring assembly
  • Figure 3 is a fragmentary cross-section, corresponding to Figure 2, of a modified form of connection.
  • A is the tubular outer casing of the turbine within which is mounted a ring of stator blades B of the kind sometimes called a nozzle ring through which the hot gases from combustion chambers, one of which is indicated at C, are delivered to a ring of rotor blades indicated at D supported upon a rotor disc D in well-known manner.
  • the gases leaving the rotor blades D then pass through a ring of stator blades E rigid with the casing A before impinging on the rotor blades F of the next stage carried by a rotor disc F
  • the blades B constituting the nozzle ring are of known hollow form and are arranged in a manner known per se and in itself forming no part of the invention, to have cooling air delivered to their inner ends through a chamber G so that this cooling air flows through the blades into an outer annular cooling air chamber H.
  • a shroud ring assembly Surrounding the ring of rotor blades D is a shroud ring assembly according to the invention comprising a supporting structure formed by the surrounding part of the casing A on which, to this end, are formed a series of circumferentially spaced bosses A and a shroud ring comprising a series of separate relatively circumferentiaily aligned arcuate sections I each of channel-shaped cross-section, as shown and of closed-ended trough-like form, the inner circumferential wall of each section being in the form a section of a frustrum of a cone, While the flanges J J on the sides of each arcuate section are located between a flange A formed on a ring A rigid with the casing A and a ring A also rigid with the casing A and serving to support the outer ends of the blades B of the nozzle ring.
  • the arcuate sections I, of the shroud ring are not gripped between the flange A and the ring A
  • each arcuate shroud ring section I Formed in one fixed end of each arcuate shroud ring section I is a boss J provided with a circumferentially extending surface 10 having formed therein a radial hole which is internally screwthreaded as shown at J to receive the inner end of a bolt K passing through one of the bosses A and serving to immovably secure that end of the shroud ring section firmly to the casing A with its surface 10 flush against the inner circumferential wall 11 of the casing as shown most clearly in Figure 2.
  • the free end of each said section is provided with a portion 12 normally abutting radially against theinner wall 11 of the casing in circumferentially sliding relation thereto.
  • each shroud ring section J adjacent to the boss I is also provided with a Step as shown at J while the opposite or free end of the shroud ring section is provided with a step J having a face or portion 13 spaced radially inwardly of its portion 12 and which, as clearly shown in Figure 2, circumferentially slidably engages and co-operates with the step I on the adjacent end of the adjacent shroud ring section to form a circumferential-sliding connection between the adjoining ring section ends prevent the endprovided with a step I from moving radially inwards beyond a predetermined small amount represented by a limited working-clearance 14 between the abutting steps I and I is such that each shroudring section I is-free, to expand circumferentially'relatively to the casing A and to the adjacent shroud ring sections while, as will be-seen, being maintained substantially in position both axially and radially and supported from the casing A at a single point by the bolt K.
  • each shroud ringsection In the arrangement shown there ismounted and located within each shroud ringsection a thin sheet metalbafile L the edge L of which is secured as by welding to-the flange J of the shroud ring section, while the edge L is spaced from the inner circumferentialwall 11 of the shroud ring section by spaced tabs L
  • Air outlet apertures M are formed in each-shroud ring section and the arrangement is such, as will be seen, that cooling air delivered to the annular chamber H is causedto flow round the baffle L and out through the exit apertures M where it enters the gas stream flowing through the turbine and, by flowing over the tips of the rotor blades, tends to assist further in the cooling of the shroud ring and to assist in the cooling of these blades.
  • bafile means represented by the battle L defines with the adjacent walls of the casing A and the shroud ring section I a narrow passage between the bafile means and the walls of the casing and shroud section, through which narrow passage the cooling air is caused to flow.
  • a shroud ring assembly for an axial flow turbine comprising a tubular cylindrical outer casing having an inner circumferential wall, and an annular shroud ring disposed coaxially within the outer casing, said shroud ring comprising a plurality of separate circumferentially aligned arcuate sections, each section having a fixed end formed with a circumferentially extending surface and a free end at its opposite circumferential extremity, means The arrangement fixedly and immovably securing the fixed end of each said section in said casing with said circumferentially extending surface flush against said inner circumferential wall of the casing, the remainder of each said section, including its free end, being disconnected from said casing, the free end of each said section being in circumferentially spaced relation tosaid fixed end of an adjoining section, and having a portion normally abutting radially against the said inner circumferential wall of the casing and having a further circumferentially extending portion radially inwardly spaced from said first mentioned portion, and
  • a shroud ring assembly as claimed in claim 1, in which the said means by which the fixed end of each arcuate section is secured to the inner circumferential wall of. the casing comprises a radially arranged bolt, engaging a bore in the appropriate end of the arcuate section.
  • a shroud ring assembly as claimed in claim 3, in which the said bore is screwthreaded and is engaged by the inner screwthreaded endv of the bolt, which passes freely through a hole in the tubular outer casing.
  • each arcuate section is of channel-shaped cross-section with the sides of the channel facing radially outwards and, the tubular outer casing includes parts rigid with it and locating the arcuate sections by engagement with the sides thereof.

Description

66- 9, 1958 R. H. D. CHAMBERLIN ETAL SHROUD RING CONSTRUCTION FOR TURBINES AND COMPRESSORS Filed Dec. 7, 1955 INVEN'TOES REGINALD H. D. cunmwzurq JncK V. BLYTHE BY M, M
Pm ATTORNEYS United States Patent SHRUUD RING CONSTRUCTION FOR TURBINES AND COMPRESSORS Reginald Henry Douglas Chamberlin, Ealing, London, and Jack Vallis Biyth, Ewell, England, assignors to D. Napier & Son Limited, London, Engiand, a British company ApplicationDecemher 7, 1955, Serial No. 551,583
Claims priority, application Great Britain December 16, 1954 5 Claims. (Cl. 253-78) This invention relates to a construction of shroud ring for turbines or compressors, that is to say the shroud ring which closely surrounds a ring of rotor blades in a turbine or compressor. It is desirable that the clearance between such a shroud ring and the tips of the rotor blades shall be maintained small and shall not vary to any large degree under different operating conditions, and it is an object of the present invention to provide a shroud ring construction which will tend to enable the clearance between the shroud ring and the tips of the rotor blades to be maintained within small limits and to prevent or reduce any tendency for the shroud ring as a whole to be distored under operating conditions.
A shroud ring assembly according to the present invention comprises a tubular outer casting, and an annular shroud ring disposed within the outer casing and comprising a series of separate arcuate circumferentiallyextending sections each of which is rigidly connected at one end only (hereinafter called the fixed end) to the tubular outer casing and is supported at its other end (hereinafter called the free end) from the fixed end of the adjacent arcuate section through a connection which allows limited free relative circumferential movement between the adjacent ends of the two arcuate sections but substantially prevents relative radial movement between such adjacent ends.
In one convenient arrangement the connection between the fixed end of each arcuate section and the free end of an adjacent arcuate section is in the form of a step on the end face of one of the sections engaging a coopcrating step on the adjacent end face of the other section, it being understood that the step is arranged so that the free end of the appropriate section is held from inward radial movement relatively to the fixed end of the other section by the inter-engaging steps.
Alternatively a key may be provided extending between and engaging axially extending slots in the adjacent ends of the two sections.
In any case each arcuate section of the shroud ring is preferably of such cross section as to provide Within it a chamber having means by which cooling air can be supplied to and permitted to escape from it. Moreover one or more sheet metal baflle members are then preferably provided within each arcuate section and arranged to define with the inner circumferential wall at least of the arcuate section a narrow passage through which the cooling air is caused by the baflle member to fioW.
Conveniently the fixed end of each arcuate section is secured to the tubular outer casing by means of a radially arranged bolt, stud, or the like engaging a bore in the appropriate end of the arcuate section. For example each of the bores in question may be screwthreaded and be engaged by the inner screwthreaded end of a bolt passing freely through a radial hole in the tubular outer casing.
In one preferred construction according to the invention Patented Dec. 9, 1958 each arcuate section of the shroud ring is of channelshaped cross-section in planes containing the axis of the tubular casing, and one construction embodying arcuate sections of this form and a modification thereof, are shown in the accompanying drawings, in which:
Figure 1 is a sectional view in a plane containing the axis of a combustion turbine of the part of such turbine including a shroud ring according to the invention and two adjacent rings of stator blades, the parts shown in the drawing being for convenience limited substantially to those necessary for an understanding of the invention itself and not representing a complete cross-section through the turbine,
Figure 2 is a cross-section on the line 22 of Figure 1 through the shroud ring assembly, and
Figure 3 is a fragmentary cross-section, corresponding to Figure 2, of a modified form of connection.
In the embodiment of the invention shown in Figures 1 and 2, A is the tubular outer casing of the turbine within which is mounted a ring of stator blades B of the kind sometimes called a nozzle ring through which the hot gases from combustion chambers, one of which is indicated at C, are delivered to a ring of rotor blades indicated at D supported upon a rotor disc D in well-known manner. The gases leaving the rotor blades D then pass through a ring of stator blades E rigid with the casing A before impinging on the rotor blades F of the next stage carried by a rotor disc F The blades B constituting the nozzle ring are of known hollow form and are arranged in a manner known per se and in itself forming no part of the invention, to have cooling air delivered to their inner ends through a chamber G so that this cooling air flows through the blades into an outer annular cooling air chamber H.
Surrounding the ring of rotor blades D is a shroud ring assembly according to the invention comprising a supporting structure formed by the surrounding part of the casing A on which, to this end, are formed a series of circumferentially spaced bosses A and a shroud ring comprising a series of separate relatively circumferentiaily aligned arcuate sections I each of channel-shaped cross-section, as shown and of closed-ended trough-like form, the inner circumferential wall of each section being in the form a section of a frustrum of a cone, While the flanges J J on the sides of each arcuate section are located between a flange A formed on a ring A rigid with the casing A and a ring A also rigid with the casing A and serving to support the outer ends of the blades B of the nozzle ring. The arcuate sections I, of the shroud ring are not gripped between the flange A and the ring A but are held in position thereby while being free to slide relatively thereto.
Formed in one fixed end of each arcuate shroud ring section I is a boss J provided with a circumferentially extending surface 10 having formed therein a radial hole which is internally screwthreaded as shown at J to receive the inner end of a bolt K passing through one of the bosses A and serving to immovably secure that end of the shroud ring section firmly to the casing A with its surface 10 flush against the inner circumferential wall 11 of the casing as shown most clearly in Figure 2. The free end of each said section is provided with a portion 12 normally abutting radially against theinner wall 11 of the casing in circumferentially sliding relation thereto.
The fixed end of each shroud ring section J adjacent to the boss I is also provided with a Step as shown at J while the opposite or free end of the shroud ring section is provided with a step J having a face or portion 13 spaced radially inwardly of its portion 12 and which, as clearly shown in Figure 2, circumferentially slidably engages and co-operates with the step I on the adjacent end of the adjacent shroud ring section to form a circumferential-sliding connection between the adjoining ring section ends prevent the endprovided with a step I from moving radially inwards beyond a predetermined small amount represented by a limited working-clearance 14 between the abutting steps I and I is such that each shroudring section I is-free, to expand circumferentially'relatively to the casing A and to the adjacent shroud ring sections while, as will be-seen, being maintained substantially in position both axially and radially and supported from the casing A at a single point by the bolt K.
In the arrangement shown there ismounted and located within each shroud ringsection a thin sheet metalbafile L the edge L of which is secured as by welding to-the flange J of the shroud ring section, while the edge L is spaced from the inner circumferentialwall 11 of the shroud ring section by spaced tabs L Air outlet apertures M are formed in each-shroud ring section and the arrangement is such, as will be seen, that cooling air delivered to the annular chamber H is causedto flow round the baffle L and out through the exit apertures M where it enters the gas stream flowing through the turbine and, by flowing over the tips of the rotor blades, tends to assist further in the cooling of the shroud ring and to assist in the cooling of these blades.
it will be apparent that the bafile means represented by the battle L defines with the adjacent walls of the casing A and the shroud ring section I a narrow passage between the bafile means and the walls of the casing and shroud section, through which narrow passage the cooling air is caused to flow.
In the modified arrangement shown in Figure 3 which is otherwise similar to that described above, instead of the adjacent ends of the shroud ring sections being provided with the cooperating steps I 1 they are formed with axially extending slots J, I lying opposite to one another, into which slots is slid a key member I which permits relative circumferential movement between the adjacent ends of the shroud ring sections while virtually preventing relative radial movement between them.
What we claim as our invention and desire to secure by Letters Patent is:
l. A shroud ring assembly for an axial flow turbine comprising a tubular cylindrical outer casing having an inner circumferential wall, and an annular shroud ring disposed coaxially within the outer casing, said shroud ring comprising a plurality of separate circumferentially aligned arcuate sections, each section having a fixed end formed with a circumferentially extending surface and a free end at its opposite circumferential extremity, means The arrangement fixedly and immovably securing the fixed end of each said section in said casing with said circumferentially extending surface flush against said inner circumferential wall of the casing, the remainder of each said section, including its free end, being disconnected from said casing, the free end of each said section being in circumferentially spaced relation tosaid fixed end of an adjoining section, and having a portion normally abutting radially against the said inner circumferential wall of the casing and having a further circumferentially extending portion radially inwardly spaced from said first mentioned portion, and a circumferential sliding connection between each free end and the said fixed end of an adjoining section, said connection being provided by disposition of said further portion of the free end in slidable overlapping relation to said fixed end in a circumferential direction, thereby permitting circumferential expansion of said free ends but preventing radial inward deflection of said free end.
2. A shroud ring assembly as claimed in claim 1, in which theconnection between the fixed end of each arcuate section and the free end of an adjacent arcuate section comprises a step on the adjacent end face of one of the sections engaging a cooperating step on the end face of the other section.
3. A shroud ring assembly as claimed in claim 1, in which the said means by which the fixed end of each arcuate section is secured to the inner circumferential wall of. the casing comprises a radially arranged bolt, engaging a bore in the appropriate end of the arcuate section.
4. A shroud ring assembly, as claimed in claim 3, in which the said bore is screwthreaded and is engaged by the inner screwthreaded endv of the bolt, which passes freely through a hole in the tubular outer casing.
5. A shroud ring assembly as claimed in claim 1, in which each arcuate section is of channel-shaped cross-section with the sides of the channel facing radially outwards and, the tubular outer casing includes parts rigid with it and locating the arcuate sections by engagement with the sides thereof.
References Cited in the file of this patent UNITED STATES PATENTS 2,510,606 Price June 6, 1950 2,584,899 McLeod Feb. 5, 1952 2,685,429 Auyer Aug. 3, 1954 FOREIGN PATENT 270,334 Switzerland Nov. 16, 1950 625,938 France May 2, 1927 679,916 Great Britain Sept. 24, 1952
US551583A 1954-12-16 1955-12-07 Shroud ring construction for turbines and compressors Expired - Lifetime US2863634A (en)

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BE (1) BE543709A (en)
CH (1) CH345766A (en)
DE (1) DE1080119B (en)
FR (1) FR1138118A (en)
GB (1) GB785466A (en)
NL (2) NL103792C (en)

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US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal
US3408044A (en) * 1965-07-23 1968-10-29 Bbc Brown Boveri & Cie Combustion gas turbine with cooled guide vane support structure
US3520635A (en) * 1968-11-04 1970-07-14 Avco Corp Turbomachine shroud assembly
US3689174A (en) * 1971-01-11 1972-09-05 Westinghouse Electric Corp Axial flow turbine structure
US3807891A (en) * 1972-09-15 1974-04-30 United Aircraft Corp Thermal response turbine shroud
US3824031A (en) * 1972-01-12 1974-07-16 Rolls Royce 1971 Ltd Turbine casing for a gas turbine engine
US3854843A (en) * 1971-12-01 1974-12-17 R Penny Composite elongate member having a predetermined effective coefficient of linear expansion
US3981609A (en) * 1975-06-02 1976-09-21 United Technologies Corporation Coolable blade tip shroud
US3986720A (en) * 1975-04-14 1976-10-19 General Electric Company Turbine shroud structure
US4013376A (en) * 1975-06-02 1977-03-22 United Technologies Corporation Coolable blade tip shroud
US4317646A (en) * 1979-04-26 1982-03-02 Rolls-Royce Limited Gas turbine engines
US4355952A (en) * 1979-06-29 1982-10-26 Westinghouse Electric Corp. Combustion turbine vane assembly
US4398864A (en) * 1979-05-02 1983-08-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Sealing device between two elements of a turbomachine
US4595345A (en) * 1979-01-15 1986-06-17 Varga John M J Gas compressor or blower
US4741669A (en) * 1983-04-27 1988-05-03 Tatsuji Shimokawabe Shroud
US5088888A (en) * 1990-12-03 1992-02-18 General Electric Company Shroud seal
US5131811A (en) * 1990-09-12 1992-07-21 United Technologies Corporation Fastener mounting for multi-stage compressor
US5145316A (en) * 1989-12-08 1992-09-08 Rolls-Royce Plc Gas turbine engine blade shroud assembly
US5158430A (en) * 1990-09-12 1992-10-27 United Technologies Corporation Segmented stator vane seal
US5180281A (en) * 1990-09-12 1993-01-19 United Technologies Corporation Case tying means for gas turbine engine
US5297932A (en) * 1990-09-12 1994-03-29 United Technologies Corporation Fastener for multi-stage compressor
US5823741A (en) * 1996-09-25 1998-10-20 General Electric Co. Cooling joint connection for abutting segments in a gas turbine engine
US6464453B2 (en) * 2000-12-04 2002-10-15 General Electric Company Turbine interstage sealing ring
US20040219009A1 (en) * 2003-03-06 2004-11-04 Snecma Moteurs Turbomachine with cooled ring segments
US20050232752A1 (en) * 2004-04-15 2005-10-20 David Meisels Turbine shroud cooling system
US9334754B2 (en) 2010-11-29 2016-05-10 Alstom Technology Ltd. Axial flow gas turbine
EP3187690A1 (en) * 2016-01-04 2017-07-05 General Electric Company System for an inlet guide vane shroud and baffle assembly
US20170218788A1 (en) * 2014-10-23 2017-08-03 Siemens Energy, Inc. Gas turbine engine with a turbine blade tip clearance control system
US20200072070A1 (en) * 2018-09-05 2020-03-05 United Technologies Corporation Unified boas support and vane platform

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DE3018621C2 (en) * 1980-05-16 1982-06-03 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Outer casing for axial compressors or turbines of flow machines, in particular gas turbine engines
US4921401A (en) * 1989-02-23 1990-05-01 United Technologies Corporation Casting for a rotary machine
US5221096A (en) * 1990-10-19 1993-06-22 Allied-Signal Inc. Stator and multiple piece seal
NL1014013C2 (en) * 2000-01-05 2001-07-18 Ventilatoren Sirocco Howden Bv Housing part for a fan impeller.
US10215192B2 (en) 2014-07-24 2019-02-26 Siemens Aktiengesellschaft Stator vane system usable within a gas turbine engine

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FR625938A (en) * 1926-03-24 1927-08-23 Rateau Sa Fixing device for dispensing nozzles for steam turbines
US2510606A (en) * 1943-05-22 1950-06-06 Lockheed Aircraft Corp Turbine construction
CH270334A (en) * 1945-01-16 1950-08-31 Power Jets Res & Dev Ltd Blade carrier in axial centrifugal machines.
US2584899A (en) * 1945-01-23 1952-02-05 Power Jets Res & Dev Ltd Construction of stator elements of turbines, compressors, or like machines
GB679916A (en) * 1949-04-29 1952-09-24 Geoffrey Bertram Robert Feilde Improvements in gas turbines
US2685429A (en) * 1950-01-31 1954-08-03 Gen Electric Dynamic sealing arrangement for turbomachines

Cited By (35)

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Publication number Priority date Publication date Assignee Title
US3408044A (en) * 1965-07-23 1968-10-29 Bbc Brown Boveri & Cie Combustion gas turbine with cooled guide vane support structure
US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal
US3520635A (en) * 1968-11-04 1970-07-14 Avco Corp Turbomachine shroud assembly
US3689174A (en) * 1971-01-11 1972-09-05 Westinghouse Electric Corp Axial flow turbine structure
US3854843A (en) * 1971-12-01 1974-12-17 R Penny Composite elongate member having a predetermined effective coefficient of linear expansion
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Also Published As

Publication number Publication date
GB785466A (en) 1957-10-30
FR1138118A (en) 1957-06-11
NL103792C (en)
CH345766A (en) 1960-04-15
BE543709A (en)
NL202529A (en)
DE1080119B (en) 1960-04-21

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