US1966104A - Turbine rotor construction - Google Patents

Turbine rotor construction Download PDF

Info

Publication number
US1966104A
US1966104A US587187A US58718732A US1966104A US 1966104 A US1966104 A US 1966104A US 587187 A US587187 A US 587187A US 58718732 A US58718732 A US 58718732A US 1966104 A US1966104 A US 1966104A
Authority
US
United States
Prior art keywords
blade
core
parts
core part
turbine rotor
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.)
Expired - Lifetime
Application number
US587187A
Inventor
Noack Walter Gustav
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.)
BBC Brown Boveri AG Germany
Original Assignee
Bbc Brown Boveri & Cie
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 Bbc Brown Boveri & Cie filed Critical Bbc Brown Boveri & Cie
Application granted granted Critical
Publication of US1966104A publication Critical patent/US1966104A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Definitions

  • one of the objects of my invention is to provide improved turbine rotor construction which has all the advantages of those proposed heretofore, but whichl does not have the disadvantages and give rise to the problems referred to.
  • each blade rtalrenon the line 5 5 in Fig.
  • each blade unit is made'in two parts, namely, a core part rigidly connected to the rotor diskl or drum and provided with passages for the cooling uid, and a. blade lpart in the form of a sheath disposed about the core part and having a relatively close iit thereon, the sheath being made of heat-resistant material.
  • the power-transmitting or core part oi each blade unit is, in effect, separate from the blade part which guides the hot driving gases.
  • Thefcore part can therefore be vrfgid y secured to the rotor disk by a strong and watertight Welded connection which need not be disturbed in making repairs, this being done by removing and replacing only the outer blade part or sheath.
  • Figure 1 is an elevational, fragmentary view, partly in section, oi a turbine rotor constructed in accordance with my invention
  • Fig. 2 is a plan View oi' Fig. l, partly in section;
  • Fig. 3 is a view similar to Fig. 2, showing a modification
  • Fig. 4 is a sectional view, the section being taken on the line 4-t in Fig. 3;
  • Fig. 5 is a sectional view, the section being 4; and Fig. 6 is a view similarV to Fig. 5, showing a modification.
  • the reference numeral 2 designates a rotor disk.
  • the core parts l of the blade units are machined out of the disk, and are each provided with a pair of longitudinal passages 3 for the ow oi cooling fluid from the interior oi' the disk into the interior of the core part, and then back into the disk.
  • Each blade part is shown as being in the form of a sheath 6 disposed about the respective core part and having a relatively close lt thereon.
  • The. sheaths 6 have the required shape for the operating surfaces of the blades, and can be bent from sheet metal and welded at one or both edges, as the case might be, or they can be pressed out from a piece of tubing.
  • the material used for the blade parts is highly resistant to heat, such es sheet steel or a sheet of any chromium or chromiuin alloy or the like.
  • a shroud ring 7 operates to held the sheaths 6 on the core parts, and is apertured to receive the outer ends 5 of the latter which are dared over the ring, as shown, to loci; the latter to the core lli) ' nect the same, and the parts.
  • the sheaths bear against the shroud ring "I under the action of the centrifugal forces.
  • each core part is bored into the outer adjacent ends of the passages 3 to conbores are then threaded to receive closing plugs 4. As indicated in Fig. 1, the plugs 4 may then be welded to the core ends 5.
  • the sheaths have a tight fit on the core parts, they are well supported and have to withstand very little force. For this reason, the sheaths can be made of thinner sheet metal and can be brought up to a very high temperature without danger. Furthermore, the amount of heat which the sheaths impart to the core parts by radiation and contact therewith is much less than would be the case if the hot driving gases came into direct contact with the cooled core parts. On account of this desirable action, it is possible to maintain the core parts at a desirable, relatively low teinperature without withdrawing an excessive amount of heat from the hot driving gases.
  • the core parts 8 are madel as separate pieces which are screwed,I as shown, into the rotor disk 9.
  • a light weld may be employed to seal the screwv connecof the forces, however, are taken up by the screw threads.
  • Plugs 11, corresponding to the plugs 4 in Figs. 1 and 2 operate to close the bores or openings which are made to connect the outer adjacent ends of the cooling passages 18 which are aligned respectively with the passages 19 in the rotor disk.
  • a suitable insert 15 separates the adjacent ends of the passages 18 and 19. ⁇
  • the blade parts are in the form of sheaths 12 of sheet metal which have a close fit on thecore parts 8, and which are welded at 13 to the disk 9. Since the sheaths 12 are relatively light, the welding is sufficient to hold them in place on the core parts, and therefore serves the same purpose as the shroud ring 'I in tion. Practically all Fig. 1, which is omitted in this construction. The' edge 14 of each blade part is sharpened, as shown more clearly in Fig. 5.
  • Fig. 6 The construction shown in Fig. 6 is similar to that in Figs. 3, 4 and 5, except that the closing plugs 16 are screwed into the ends of the core parts, as in Figs. 1 and 2, and then welded, as indicated. This welding also serves to x the outer end of the blade part 17 to the core part, and is the only point of fixation between these parts.
  • the blade part therefore, which is heated to a higher temperature than the core part, is free to expand from the outer point of fixation thereof with the core part, and is made slightly shorter, as shown, to prevent distortion.
  • a rotor niember provided with blade units, said units comvsheath disposed about prising a supporting core part and a separate structural piece of relatively high heat-resistive material providing a blade part in the form of a and having a relatively close fit on the core part, said rotor construction being provided with passages for the flow of cooling fluid from the interior of said rotor member to the interior of said core parts.
  • a rotor member provided with blade units, said units comprising a supporting core part provided with a passage for a cooling fluid, and a separate structural piece providing a blade part in the form of a sheath having a relatively close fit on said core part and made of relatively high heat-resistive material.
  • a rotor member provided with blade units, said units comprising a supporting core part and a blade part fitted to said core part for longitudinal movement relatively with respect thereto due to occurring unequal expansion and contraction or said parts, said blade part being xed only at one end thereof to said core part to permit such unequal expansion and contraction.
  • a rotor mem- ⁇ ber provided with blade units, said units comprising a supporting core part and a blade part in the form of' a sheath disposed about the core part and fitted thereto for longitudinal movement relatively with respect to said core part due to occurring unequal expansion and contraction of said parts, said blade part being fixed to said core part only at the outer end of the latter, the length of said blade part, measured inwardly from the point of fixation thereof being less than such length of said core part.
  • a rotor member provided with blade units.
  • said units comprising a supporting core part and a separate structural piece providing a blade part in the form of a sheath disposedabout the core part, said rotor construction being provided with passages for the flow of cooling fluid from the ⁇ interior of said rotor member to the interior of said core parts, and an apertured element for holding the sheaths on the core parts, the outer ends of said core parts extending through the apertures in said element and locked over the latter.
  • a rotor member provided with blade units, said units comprising a supporting core part provided with a pair of longitudinal passages and a blade part in the form of a sheath disposed about and havy ing a relatively close fit on the core part, an apertured element for holding the sheaths on the core parts, the outer ends of said core parts extending through the apertures in said element and being flared into said element, the flared end of each core part being provided with an opening communicating with the adjacent outer ends of the longitudinal passages, and means closing said openings.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

July 10, 1934. w. G. NoAcK TURBINE ROTOR CONSTRUCTION Filed Jan. 18, 1932 `Patented July li), 1934 1,966,104 rename Boron ooNs'raoorroN Walter Gustav pany of Switzerland Application Noack, Baden, signor to Aktiengesellschaft Cie., Baden, Switzerl January 1e, 1932, serial e110.
Switzerland, as- Brown Boverl &
and, a joint-stock com- In Germany January 19, 193 6 `Claims. (Cl. 253-77) My invention relates to improvements in tur.-
lbine rotor constructions.
In turbines constructed heretofore, vand particularly those wherein the driving medium is aV gas, diiiicuty has beeny experienced due to some manner of failure of the blades either directly or indirectly on account of the extremely high ternperatures necessary for ecient operation. To avoid this, it has been proposed to make the blades hollow, or to bore out solid blades and thereby provide passages through whichwater or air can be circulated for cooling purposes. There was then the problem of connecting the cooled blades to the rotor disk or drum so that the connectons would be strong enough to Withstand the high centrifugal forces on the blades themselves and would also be tight enough to prevent leakage of the cooling water at the connections under the high pressure to which the water was raised by the high peripheral velocity. Weding was resorted to for the purpose of making the tension-resisting and watertight connect? ons between the blades and the rotor disk. The welded connections or joints were satisfactory for these purposes, but they made removal and replacement of the blades very diiiicult, if not impossible.
Furthermore, in the various constructions reierred to, there were high losses due to the cooling action, particularly when the hot driving gases performed work in more than one stage or ring of blades. That is, the high velocity at which the hot gases flowed through the blade passages was accompanied by a corresponding high rate of heat transfer to the blade walls. For this reason, a high percentage of the available heat energy was conducted through the blade walls and Wasted by dissipation in the cooling water. In other words, there was found to be the problem of causing cooling of the blades only to the point necessary for protection oi those parts oi the blades which were subjected to great mechanical stresses, and, with Athis in mind, the problem of limiting the rate of heat-conduction from the hot driving gases to the stressed blade parts.
With all the foregoing in mind, one of the objects of my invention is to provide improved turbine rotor construction which has all the advantages of those proposed heretofore, but whichl does not have the disadvantages and give rise to the problems referred to.
Other objects and advantages will hereinafter appear.
in accordance with my invention, each blade rtalrenon the line 5 5 in Fig.
unit is made'in two parts, namely, a core part rigidly connected to the rotor diskl or drum and provided with passages for the cooling uid, and a. blade lpart in the form of a sheath disposed about the core part and having a relatively close iit thereon, the sheath being made of heat-resistant material. In this way, the power-transmitting or core part oi each blade unit is, in effect, separate from the blade part which guides the hot driving gases. Thefcore part can therefore be vrfgid y secured to the rotor disk by a strong and watertight Welded connection which need not be disturbed in making repairs, this being done by removing and replacing only the outer blade part or sheath.
- My invention resides in the improved construction oi the character hereinafter described and claimed.
For the purpose of illustrating my invention, an embodiment thereof is shown in the drawing, wherein Figure 1 is an elevational, fragmentary view, partly in section, oi a turbine rotor constructed in accordance with my invention;
Fig. 2 is a plan View oi' Fig. l, partly in section;
Fig. 3 is a view similar to Fig. 2, showing a modification;
Fig. 4 is a sectional view, the section being taken on the line 4-t in Fig. 3;
Fig. 5 is a sectional view, the section being 4; and Fig. 6 is a view similarV to Fig. 5, showing a modification.
Referring to Fig. l, the reference numeral 2 designates a rotor disk. The core parts l of the blade units are machined out of the disk, and are each provided with a pair of longitudinal passages 3 for the ow oi cooling fluid from the interior oi' the disk into the interior of the core part, and then back into the disk.
Each blade part is shown as being in the form of a sheath 6 disposed about the respective core part and having a relatively close lt thereon. The. sheaths 6 have the required shape for the operating surfaces of the blades, and can be bent from sheet metal and welded at one or both edges, as the case might be, or they can be pressed out from a piece of tubing. The material used for the blade parts is highly resistant to heat, such es sheet steel or a sheet of any chromium or chromiuin alloy or the like.
A shroud ring 7 operates to held the sheaths 6 on the core parts, and is apertured to receive the outer ends 5 of the latter which are dared over the ring, as shown, to loci; the latter to the core lli) ' nect the same, and the parts. In operation, the sheaths bear against the shroud ring "I under the action of the centrifugal forces.
The outer end of each core part is bored into the outer adjacent ends of the passages 3 to conbores are then threaded to receive closing plugs 4. As indicated in Fig. 1, the plugs 4 may then be welded to the core ends 5.
As the sheaths have a tight fit on the core parts, they are well supported and have to withstand very little force. For this reason, the sheaths can be made of thinner sheet metal and can be brought up to a very high temperature without danger. Furthermore, the amount of heat which the sheaths impart to the core parts by radiation and contact therewith is much less than would be the case if the hot driving gases came into direct contact with the cooled core parts. On account of this desirable action, it is possible to maintain the core parts at a desirable, relatively low teinperature without withdrawing an excessive amount of heat from the hot driving gases.
In the embodiment of my invention shown in Figs. 3, 4 and 5, the core parts 8 are madel as separate pieces which are screwed,I as shown, into the rotor disk 9. As indicated at 10, a light weld may be employed to seal the screwv connecof the forces, however, are taken up by the screw threads. Plugs 11, corresponding to the plugs 4 in Figs. 1 and 2, operate to close the bores or openings which are made to connect the outer adjacent ends of the cooling passages 18 which are aligned respectively with the passages 19 in the rotor disk. A suitable insert 15 separates the adjacent ends of the passages 18 and 19.`
As in Figs. 1 and 2, the blade parts are in the form of sheaths 12 of sheet metal which have a close fit on thecore parts 8, and which are welded at 13 to the disk 9. Since the sheaths 12 are relatively light, the welding is sufficient to hold them in place on the core parts, and therefore serves the same purpose as the shroud ring 'I in tion. Practically all Fig. 1, which is omitted in this construction. The' edge 14 of each blade part is sharpened, as shown more clearly in Fig. 5.
The construction shown in Fig. 6 is similar to that in Figs. 3, 4 and 5, except that the closing plugs 16 are screwed into the ends of the core parts, as in Figs. 1 and 2, and then welded, as indicated. This welding also serves to x the outer end of the blade part 17 to the core part, and is the only point of fixation between these parts.
' The blade part, therefore, which is heated to a higher temperature than the core part, is free to expand from the outer point of fixation thereof with the core part, and is made slightly shorter, as shown, to prevent distortion.
Other modifications, within the conception of those Askilled in the art, are possible without departing from the spirit of my invention or the scope of the claims.
I claim as my invention:-
1. In turbine rotor construction, a rotor niember provided with blade units, said units comvsheath disposed about prising a supporting core part and a separate structural piece of relatively high heat-resistive material providing a blade part in the form of a and having a relatively close fit on the core part, said rotor construction being provided with passages for the flow of cooling fluid from the interior of said rotor member to the interior of said core parts.
2. In turbine rotor construction, a rotor member provided with blade units, said units comprising a supporting core part provided with a passage for a cooling fluid, and a separate structural piece providing a blade part in the form of a sheath having a relatively close fit on said core part and made of relatively high heat-resistive material.
3. In turbine rotor construction, a rotor member provided with blade units, said units comprising a supporting core part and a blade part fitted to said core part for longitudinal movement relatively with respect thereto due to occurring unequal expansion and contraction or said parts, said blade part being xed only at one end thereof to said core part to permit such unequal expansion and contraction.
4. In turbine rotor construction, a rotor mem-` ber provided with blade units, said units comprising a supporting core part and a blade part in the form of' a sheath disposed about the core part and fitted thereto for longitudinal movement relatively with respect to said core part due to occurring unequal expansion and contraction of said parts, said blade part being fixed to said core part only at the outer end of the latter, the length of said blade part, measured inwardly from the point of fixation thereof being less than such length of said core part.
5. In turbine rotor construction, a rotor member provided with blade units. said units comprising a supporting core part and a separate structural piece providing a blade part in the form of a sheath disposedabout the core part, said rotor construction being provided with passages for the flow of cooling fluid from the` interior of said rotor member to the interior of said core parts, and an apertured element for holding the sheaths on the core parts, the outer ends of said core parts extending through the apertures in said element and locked over the latter.
6. In turbine rotor construction, a rotor member provided with blade units, said units comprising a supporting core part provided with a pair of longitudinal passages and a blade part in the form of a sheath disposed about and havy ing a relatively close fit on the core part, an apertured element for holding the sheaths on the core parts, the outer ends of said core parts extending through the apertures in said element and being flared into said element, the flared end of each core part being provided with an opening communicating with the adjacent outer ends of the longitudinal passages, and means closing said openings.
' WALTER GUSTAV NOACK.
locking engagement with
US587187A 1931-01-19 1932-01-18 Turbine rotor construction Expired - Lifetime US1966104A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE1966104X 1931-01-19

Publications (1)

Publication Number Publication Date
US1966104A true US1966104A (en) 1934-07-10

Family

ID=7816536

Family Applications (1)

Application Number Title Priority Date Filing Date
US587187A Expired - Lifetime US1966104A (en) 1931-01-19 1932-01-18 Turbine rotor construction

Country Status (1)

Country Link
US (1) US1966104A (en)

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2448825A (en) * 1944-03-20 1948-09-07 Lockheed Aircraft Corp Turbine rotor
US2454580A (en) * 1943-03-18 1948-11-23 Gen Electric Method of manufacturing bladed rotors
US2463340A (en) * 1945-02-22 1949-03-01 Wiberg Oscar Anton Axial flow turbine blade structure
US2479057A (en) * 1945-03-27 1949-08-16 United Aircraft Corp Turbine rotor
US2500745A (en) * 1944-09-21 1950-03-14 Gen Electric Bucket structure for high-temperature turbomachines
US2501038A (en) * 1947-03-29 1950-03-21 United Aircraft Corp Mounting for hollow turbine blades
US2553078A (en) * 1947-03-29 1951-05-15 United Aircraft Corp Turbine blade mounting
US2563269A (en) * 1943-05-22 1951-08-07 Lockheed Aircraft Corp Gas turbine
US2568726A (en) * 1949-08-03 1951-09-25 Franz Anselm Air-cooled turbine blade
US2648520A (en) * 1949-08-02 1953-08-11 Heinz E Schmitt Air-cooled turbine blade
US2690132A (en) * 1951-07-30 1954-09-28 Packard Motor Car Co Rotatable vaned element
US2696364A (en) * 1948-07-08 1954-12-07 Thompson Prod Inc Turbine bucket
US2738950A (en) * 1945-12-13 1956-03-20 Lockheed Aircraft Corp Turbine machine having high velocity blading
US2778601A (en) * 1951-05-28 1957-01-22 Ernst R G Eckert Fluid cooled turbine blade construction
US2779565A (en) * 1948-01-05 1957-01-29 Bruno W Bruckmann Air cooling of turbine blades
US2836391A (en) * 1951-10-10 1958-05-27 Gen Motors Corp Turbine bucket with cast-in insert
US2868500A (en) * 1949-02-15 1959-01-13 Boulet George Cooling of blades in machines where blading is employed
US2920865A (en) * 1952-10-31 1960-01-12 Rolls Royce Bladed stator or rotor constructions with means to supply a fluid internally of the blades
US3192862A (en) * 1961-03-13 1965-07-06 Rockwell Standard Co Bladed element for fluid torque converters and the like
US3240153A (en) * 1961-12-28 1966-03-15 Rockwell Standard Co Hydrodynamic bladed wheel assemblies
US3802046A (en) * 1972-01-27 1974-04-09 Chromalloy American Corp Method of making or reconditioning a turbine-nozzle or the like assembly
US20120201662A1 (en) * 2011-02-04 2012-08-09 Lutjen Paul M Core runout ceiling for turbine components
DE102020120365A1 (en) 2020-08-03 2022-02-03 Iav Gmbh Ingenieurgesellschaft Auto Und Verkehr Multi-part blade with cooling for turbomachines

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2454580A (en) * 1943-03-18 1948-11-23 Gen Electric Method of manufacturing bladed rotors
US2563269A (en) * 1943-05-22 1951-08-07 Lockheed Aircraft Corp Gas turbine
US2448825A (en) * 1944-03-20 1948-09-07 Lockheed Aircraft Corp Turbine rotor
US2500745A (en) * 1944-09-21 1950-03-14 Gen Electric Bucket structure for high-temperature turbomachines
US2463340A (en) * 1945-02-22 1949-03-01 Wiberg Oscar Anton Axial flow turbine blade structure
US2479057A (en) * 1945-03-27 1949-08-16 United Aircraft Corp Turbine rotor
US2738950A (en) * 1945-12-13 1956-03-20 Lockheed Aircraft Corp Turbine machine having high velocity blading
US2553078A (en) * 1947-03-29 1951-05-15 United Aircraft Corp Turbine blade mounting
US2501038A (en) * 1947-03-29 1950-03-21 United Aircraft Corp Mounting for hollow turbine blades
US2779565A (en) * 1948-01-05 1957-01-29 Bruno W Bruckmann Air cooling of turbine blades
US2696364A (en) * 1948-07-08 1954-12-07 Thompson Prod Inc Turbine bucket
US2868500A (en) * 1949-02-15 1959-01-13 Boulet George Cooling of blades in machines where blading is employed
US2648520A (en) * 1949-08-02 1953-08-11 Heinz E Schmitt Air-cooled turbine blade
US2568726A (en) * 1949-08-03 1951-09-25 Franz Anselm Air-cooled turbine blade
US2778601A (en) * 1951-05-28 1957-01-22 Ernst R G Eckert Fluid cooled turbine blade construction
US2690132A (en) * 1951-07-30 1954-09-28 Packard Motor Car Co Rotatable vaned element
US2836391A (en) * 1951-10-10 1958-05-27 Gen Motors Corp Turbine bucket with cast-in insert
US2920865A (en) * 1952-10-31 1960-01-12 Rolls Royce Bladed stator or rotor constructions with means to supply a fluid internally of the blades
US3192862A (en) * 1961-03-13 1965-07-06 Rockwell Standard Co Bladed element for fluid torque converters and the like
US3240153A (en) * 1961-12-28 1966-03-15 Rockwell Standard Co Hydrodynamic bladed wheel assemblies
US3802046A (en) * 1972-01-27 1974-04-09 Chromalloy American Corp Method of making or reconditioning a turbine-nozzle or the like assembly
US20120201662A1 (en) * 2011-02-04 2012-08-09 Lutjen Paul M Core runout ceiling for turbine components
US8716623B2 (en) * 2011-02-04 2014-05-06 United Technologies Corporation Core runout ceiling for turbine components
DE102020120365A1 (en) 2020-08-03 2022-02-03 Iav Gmbh Ingenieurgesellschaft Auto Und Verkehr Multi-part blade with cooling for turbomachines

Similar Documents

Publication Publication Date Title
US1966104A (en) Turbine rotor construction
US3817654A (en) Turbine rotor cooling mechanism
US4087199A (en) Ceramic turbine shroud assembly
US5358379A (en) Gas turbine vane
US7338253B2 (en) Resilient seal on trailing edge of turbine inner shroud and method for shroud post impingement cavity sealing
US3994622A (en) Coolable turbine blade
US9217441B2 (en) Pump seal with thermal retracting actuator
US3318573A (en) Apparatus for maintaining rotor disc of gas turbine engine at a low temperature
US6575704B1 (en) Turbomachine and sealing element for a rotor thereof
US20030202876A1 (en) Attachment of a ceramic shroud in a metal housing
JPS61157703A (en) Stator assembly for rotaty machine
KR19990014273A (en) Gas turbine
US4078812A (en) Combined seal and guide arrangement for two coaxially arranged machine parts
CA2598987C (en) Sealing element for use in a fluid-flow machine
US2552239A (en) Turbine rotor cooling arrangement
US20140271294A1 (en) Pump seal with thermal retracting actuator
JPS648173B2 (en)
US3412977A (en) Segmented annular sealing ring and method of its manufacture
CA2031085A1 (en) Arrangement for sealing gaps between adjacent circumferential segments of turbine nozzles and shrouds
US10563529B2 (en) Turbine and turbine stator blade
US2451261A (en) High and low pressure turbine rotor cooling arrangement
US4256171A (en) Regenerator seal hub gas passages
EP3047130B1 (en) A gas turbine seal assembly comprising splined honeycomb seals
US2434901A (en) Turbine cooling
Bayley et al. A review of liquid cooling of high-temperature gas-turbine rotor blades