US3680979A - Rotor structure for turbo machines - Google Patents
Rotor structure for turbo machines Download PDFInfo
- Publication number
- US3680979A US3680979A US78728A US3680979DA US3680979A US 3680979 A US3680979 A US 3680979A US 78728 A US78728 A US 78728A US 3680979D A US3680979D A US 3680979DA US 3680979 A US3680979 A US 3680979A
- Authority
- US
- United States
- Prior art keywords
- bolt
- sleeve
- thru
- sleeve member
- assembly
- 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
Links
- 238000006073 displacement reaction Methods 0.000 claims description 7
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
- F04D29/286—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors multi-stage rotors
Definitions
- support sleeve is fixed on the bolt passing through the assembly of wheels.
- a second sleeve is fixed within the assembly of wheels and has aninterlocking connection with the support sleeve which serves to restrain the thru-bolt from becoming eccentric to the wheel assembly, and to increase the natural frequency of the bolt to avoid operation at resonant conditions.
- turbomachines of the multistage type as centrifugal compressors, axial flow compressors and turbines
- rotors of the composite structure wherein the wheels are arranged in stack formation between stub shafts, which are fixed to the ends of a thru-bolt, sometimes referred to as a tie-bolt.
- the wheel members in centrifugal gas compressors take the form of impellers.
- the wheels consist of bladed disks.
- the wheel assembly has an axially extending bore passage having clearance with the thrubolt.
- This invention has as an object a structure which maintains the thru-bolt centered within the rotor structure, and serves to stiffen the thru-bolt to increase the natural frequency thereof to avoid resonance at operating conditions.
- a thru-bolt support sleeve member is fixed to the bolt in the medial area thereof as by shrink fit.
- the sleeve is located within the bore passage of the wheel assembly and has close initial clearance therewith.
- a second sleeve member is also positioned intermediate the thru-bolt and the bore passage of the assembly.
- the second sleeve is fixed to one of the members of the assembly, as by shrink fit, and has running clearance with the bolt.
- the two sleeve members have interlocking portions which serve to prevent radial displacement of the thru-bolt relative to the impeller, wheel assembly, or other part to which it may be attached.
- FIG. 1 is a foreshortened lengthwise sectional view of a rotor structure in which our invention is incorporated;
- FIG. 2 is an enlarged sectional view of the seal member and contiguous portion of the thru-bolt as shown in the upper center portion of FIG. 1;
- FIG. 3 is an enlarged view in perspective of the support sleeve which is fixed to the thru-bolt;
- FIG. 4 is a view similar to FIG. 3 of the sleeve member fixedly mounted within the seal sleeve.
- the composite rotor structure shown, as an example in FIG. 1, is incorporated in a multistage twin type centrifugal gas compressor.
- the rotor includes stub shafts 10, 11 fixedly secured to the ends of the thru-bolt 12.
- a group 13 of impellers is positioned about the end por-i tion of the thru-bolt attached to the stub shaft 10, and a second group 14 of impellers is mounted in proximity to the stub shaft 11.
- a cylindrical seal member 17 is positioned intermediate the groups of impellers 13,14.
- FIG. 1 In the foreshortenedview, FIG. 1,- only the first and last stage impellers 18,19 are shown in the group 13, and in like manner, the first and last stage impellers 20,21 in the group 14.
- the impellers abutting against the stub shafts 10,11 are impellers 18 and 20, and the stub shafts are formed with shoulder structures 25. Also, the abutting areas between the respective impellers are formed with similar shoulder areas 27. Also, there is a shoulder engagement 30 between the ends of the seal member 17 and the adjacent impellers 19,21.
- the shoulder structures 25,27,30 serve to center the impellers and the seal member 17, maintaining the impellers and the seal member in coaxial alignment.
- Driving means in the form of pins 31 are positioned intermediate the impellers and stub shafts and seal member 17, the pins 31 serving to provide a driving connection to the impellers.
- the stub shafts 10,11 are threaded onto the ends of the thru-bolt 12 whereby the impellers and sleeve member 17 are compressed axially to form a rigid structure for rotationin unison.
- the thru-bolt 12 is of appreciable length, especially in view of the fact that the compressor is of the multistage type, and furthermore, is of the twin type having the separated impeller groups 13 and 14.
- Such long thru-bolts result in bolt resonance and imbalance at the high speeds at which these rotor assemblies are operated.
- This invention is directed to a structural arrangement wherein deflection or radial displacement of the thru-bolt is prevented, the bolt being maintained centered with the rotor structure, and also stiffened to increase the natural frequency of the bolt which avoids resonance thereof at operating speeds.
- a support sleeve 37 is fixedly mounted on the thrubolt as by being shrunk thereon. Other than the area contacted by the bolt, the bore 40 of the support sleeve has clearance with the periphery of the shaft 12, see FIG. 2. The support sleeve 37 also has a slight clearance with the bore of the seal member 17.
- a second sleeve member 43 is fixedly mounted in the seal 17. This sleeve 43 is formed with a shrink fit in the areas 44,45. The bore 47 of the sleeve 43 also has clearance with the thru-bolt 12.
- the sleeves 37,43 are formed with interlocking portions.
- the sleeve 37 is formed with four notches 48 extending inwardly from the end of the sleeve confronting the sleeve 43.
- the sleeve 43 is formed with axially extending projections 50.
- the projections 50 are dimensioned and spaced complemental to the notches 48 in sleeve 37, whereby the sleeves 37,43 are interlocked, and it will be apparent that this interlocking structure prevents radial displacement between thru-bolt 12 and the seal member 17. While this arrangement maintains the thru-bolt centered in the impeller assembly, it permits and accommodates radial and axial growth of the parts, as shaft 12, seal member 17, and sleeves 37,43, as by temperature change and centrifugal force.
- the rotor structure is assembled by arranging the impeller in the groups 13,14 in stack formation.
- the support sleeve 37 is heated and positioned on the thru-bolt 12 with the end of the sleeve engaging the shoulder 51 formed on the bolt 12. Upon cooling, the sleeve has a tight shrink fit with the bolt.
- the bolt with the sleeve 37 shrunk thereon, is threaded into the stub shaft 10.
- the stack of impellers in the group 13 is sleeved over the bolt against the stub shaft 10.
- the seal member 17 is heated and passed over the sleeve 37 in abutting relation with the impeller 19, thereupon the sleeve 43 is positioned in the seal member 17 with the cylindrical portion 45 thereof abutting against the shoulder 55 formed in the bore of the member 17.
- the stack of impellers 14 is then positioned against the seal 17 and the stub shaft member 1 1 is threaded on the thru-bolt.
- a procedure is employed in this last step which results in the compression of the impeller assemblies and seal member 17 being of predetermined value.
- the notch and projection arrangement 48,50 prevents any relative radial displacement between the sleeve members and, accordingly, between the thrubolt 12 andthe rotor structure, maintaining concentricity of these parts, while permitting symmetrical relaand contraction of the parts.
- a rotor structure comprising a thru-bolt, a stub shaft fixed to each end of said thru-bolt, an assembly of wheels mounted intermediate said stub shafts and being fixedly secured thereto, said rotor structure also including a seal sleeve member disposed in the center area of said wheel assembly and fixedly secured thereto, said assembly being formed with a bore passage spaced concentrically about said thru-bolt, a support sleeve member fixed to said thru-bolt and having clearance with said bore passage, a second sleeve member mounted in said borepassage, said second sleeve being disposed axially of said support sleeve and being fixedly secured to said seal sleeve member, said second sleeve member encircling said thru-bolt in concentrically spaced relation thereto, the confronting ends of said sleeves being formed with interlocking means operable to restrain said thru-bolt from radial displacement relativ to said second sleeve ember.
- interlocking means is formed with engaging portions permitting change in radial dimension in said seal sleeve member, thru-bolt and support sleeve and second sleeve due to change in temperature or centrifugal force.
- one of said sleeve members is formed at the end thereof confronting said other sleeve member with a plurality of notches spaced apart circumferentially, said other sleeve member being formed with axially extending projections positioned in said notches.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims (4)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US7872870A | 1970-10-07 | 1970-10-07 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3680979A true US3680979A (en) | 1972-08-01 |
Family
ID=22145869
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US78728A Expired - Lifetime US3680979A (en) | 1970-10-07 | 1970-10-07 | Rotor structure for turbo machines |
Country Status (4)
Country | Link |
---|---|
US (1) | US3680979A (en) |
JP (1) | JPS5036683B1 (en) |
FR (1) | FR2111096A5 (en) |
GB (1) | GB1296300A (en) |
Cited By (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3749516A (en) * | 1971-10-06 | 1973-07-31 | Carrier Corp | Rotor structure for turbo machines |
US3941506A (en) * | 1974-09-05 | 1976-03-02 | Carrier Corporation | Rotor assembly |
US3976399A (en) * | 1970-07-09 | 1976-08-24 | Kraftwerk Union Aktiengesellschaft | Rotor of disc construction for single-shaft gas turbine |
US4247256A (en) * | 1976-09-29 | 1981-01-27 | Kraftwerk Union Aktiengesellschaft | Gas turbine disc rotor |
US4537560A (en) * | 1984-05-29 | 1985-08-27 | General Electric Company | Radial key for steam turbine wheels |
US4682934A (en) * | 1985-12-06 | 1987-07-28 | General Electric Company | Wheel anti-rotation means |
US4832574A (en) * | 1988-02-12 | 1989-05-23 | United Technologies Corporation | Turbine disk securing and removal apparatus |
US4934138A (en) * | 1988-12-06 | 1990-06-19 | Allied-Signal Inc. | High temperature turbine engine structure |
US5020932A (en) * | 1988-12-06 | 1991-06-04 | Allied-Signal Inc. | High temperature ceramic/metal joint structure |
US5031400A (en) * | 1988-12-09 | 1991-07-16 | Allied-Signal Inc. | High temperature turbine engine structure |
US5232336A (en) * | 1991-06-28 | 1993-08-03 | Asea Brown Boveri Ltd. | Drum rotor for axial flow turbomachine |
US6439849B1 (en) * | 2001-05-03 | 2002-08-27 | Bell Helicopter Textron, Inc. | Dual trunnion hub-to-mast assembly |
US20040007830A1 (en) * | 2001-10-10 | 2004-01-15 | Kazuo Uematsu | Sealing structure of spindle bolt, and gas turbine |
EP1758429A1 (en) * | 2005-08-26 | 2007-02-28 | Snecma | Heating device for a cylindrical part and use thereof in the assembly of an inter-axle bearing for a multi-stage turbine machine |
EP1970530A1 (en) * | 2007-03-12 | 2008-09-17 | Siemens Aktiengesellschaft | Rotor of a thermal fluid flow engine and fluid flow engine |
US20100143149A1 (en) * | 2007-03-12 | 2010-06-10 | Francois Benkler | Turbine with at least one rotor which comprises rotor disks and a tie-bolt |
US20100158699A1 (en) * | 2008-12-22 | 2010-06-24 | Jerzy Makuszewski | Rotor mounting system for gas turbine engine |
US20100290911A1 (en) * | 2008-03-26 | 2010-11-18 | Man Diesel & Turbo Se | Turbine Rotor for a Gas Turbine |
WO2014096036A1 (en) * | 2012-12-19 | 2014-06-26 | Siemens Aktiengesellschaft | Seal of a compressor rotor |
CN104389644A (en) * | 2014-11-15 | 2015-03-04 | 哈尔滨广瀚燃气轮机有限公司 | Sealing structure for novel turbine motor torsion bearing rotor |
US20160130948A1 (en) * | 2013-07-04 | 2016-05-12 | Siemens Aktiengesellschaft | Rotor for a turbine |
CN107023321A (en) * | 2017-05-31 | 2017-08-08 | 深圳智慧能源技术有限公司 | The centering torsion pass of multistage high speed turbine machine is locked mechanism |
US9797255B2 (en) | 2011-12-14 | 2017-10-24 | Nuovo Pignone S.P.A. | Rotary machine including a machine rotor with a composite impeller portion and a metal shaft portion |
US9810235B2 (en) | 2009-11-23 | 2017-11-07 | Massimo Giannozzi | Mold for a centrifugal impeller, mold inserts and method for building a centrifugal impeller |
US9810230B2 (en) | 2009-05-08 | 2017-11-07 | Nuovo Pignone Srl | Impeller for a turbomachine and method for attaching a shroud to an impeller |
US9816518B2 (en) | 2009-11-23 | 2017-11-14 | Massimo Giannozzi | Centrifugal impeller and turbomachine |
US11162505B2 (en) | 2013-12-17 | 2021-11-02 | Nuovo Pignone Srl | Impeller with protection elements and centrifugal compressor |
IT202100010781A1 (en) * | 2021-04-28 | 2022-10-28 | Nuovo Pignone Tecnologie Srl | ROTOR OF TURBO MACHINE WITH STACKED IMPELLERS AND TURBO MACHINE |
US20240026789A1 (en) * | 2020-09-03 | 2024-01-25 | Siemens Energy Global GmbH & Co. KG | Rotor assembly for a gas turbine |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IT1135752B (en) * | 1981-04-17 | 1986-08-27 | Nuovo Pignone Spa | IMPROVEMENTS IN THE POWER STAGE OF A GAS TURBINE |
EP1970532A1 (en) * | 2007-03-12 | 2008-09-17 | Siemens Aktiengesellschaft | Rotor of a thermal fluid flow engine and gas turbine |
WO2016060686A1 (en) * | 2014-10-17 | 2016-04-21 | Siemens Aktiengesellschaft | Gas turbine spindle bolt with shrink fitted sleeve |
FR3039857B1 (en) * | 2015-08-04 | 2019-09-13 | Safran Aircraft Engines | METHOD AND DEVICE FOR CLAMPING A ROTOR LINE OF TURBOMACHINE |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1551402A (en) * | 1925-08-25 | Botob fob elastic-pi | ||
GB586200A (en) * | 1944-07-21 | 1947-03-11 | Karl Baumann | Improvements in bladed drum-type rotor constructions operating under high temperature conditions |
US3304052A (en) * | 1965-03-30 | 1967-02-14 | Westinghouse Electric Corp | Rotor structure for an elastic fluid utilizing machine |
US3356339A (en) * | 1966-12-12 | 1967-12-05 | Gen Motors Corp | Turbine rotor |
-
1970
- 1970-10-07 US US78728A patent/US3680979A/en not_active Expired - Lifetime
-
1971
- 1971-07-02 GB GB1296300D patent/GB1296300A/en not_active Expired
- 1971-08-13 JP JP46061596A patent/JPS5036683B1/ja active Pending
- 1971-10-07 FR FR7136092A patent/FR2111096A5/fr not_active Expired
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1551402A (en) * | 1925-08-25 | Botob fob elastic-pi | ||
GB586200A (en) * | 1944-07-21 | 1947-03-11 | Karl Baumann | Improvements in bladed drum-type rotor constructions operating under high temperature conditions |
US3304052A (en) * | 1965-03-30 | 1967-02-14 | Westinghouse Electric Corp | Rotor structure for an elastic fluid utilizing machine |
US3356339A (en) * | 1966-12-12 | 1967-12-05 | Gen Motors Corp | Turbine rotor |
Cited By (54)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3976399A (en) * | 1970-07-09 | 1976-08-24 | Kraftwerk Union Aktiengesellschaft | Rotor of disc construction for single-shaft gas turbine |
US3749516A (en) * | 1971-10-06 | 1973-07-31 | Carrier Corp | Rotor structure for turbo machines |
US3941506A (en) * | 1974-09-05 | 1976-03-02 | Carrier Corporation | Rotor assembly |
US4247256A (en) * | 1976-09-29 | 1981-01-27 | Kraftwerk Union Aktiengesellschaft | Gas turbine disc rotor |
US4537560A (en) * | 1984-05-29 | 1985-08-27 | General Electric Company | Radial key for steam turbine wheels |
US4682934A (en) * | 1985-12-06 | 1987-07-28 | General Electric Company | Wheel anti-rotation means |
US4832574A (en) * | 1988-02-12 | 1989-05-23 | United Technologies Corporation | Turbine disk securing and removal apparatus |
US4934138A (en) * | 1988-12-06 | 1990-06-19 | Allied-Signal Inc. | High temperature turbine engine structure |
US5020932A (en) * | 1988-12-06 | 1991-06-04 | Allied-Signal Inc. | High temperature ceramic/metal joint structure |
US5031400A (en) * | 1988-12-09 | 1991-07-16 | Allied-Signal Inc. | High temperature turbine engine structure |
US5232336A (en) * | 1991-06-28 | 1993-08-03 | Asea Brown Boveri Ltd. | Drum rotor for axial flow turbomachine |
US6439849B1 (en) * | 2001-05-03 | 2002-08-27 | Bell Helicopter Textron, Inc. | Dual trunnion hub-to-mast assembly |
WO2002090183A1 (en) * | 2001-05-03 | 2002-11-14 | Bell Helicopter Textron Inc. | Dual trunnion hub-to-mast assembly |
EP1435431A1 (en) * | 2001-10-10 | 2004-07-07 | Mitsubishi Heavy Industries, Ltd. | Sealing structure of spindle bolt, and gas turbine |
EP1435431A4 (en) * | 2001-10-10 | 2010-06-16 | Mitsubishi Heavy Ind Ltd | Sealing structure of spindle bolt, and gas turbine |
US6991429B2 (en) * | 2001-10-10 | 2006-01-31 | Mitsubishi Heavy Industries, Ltd. | Sealing structure of spindle bolt, and gas turbine |
CN1322225C (en) * | 2001-10-10 | 2007-06-20 | 三菱重工业株式会社 | Sealing structure of spindle bolt and gas turbine |
US20070234703A1 (en) * | 2001-10-10 | 2007-10-11 | Mitsubishi Heavy Industries Ltd. | Sealing structure of spindle bolt, and gas turbine |
US20040007830A1 (en) * | 2001-10-10 | 2004-01-15 | Kazuo Uematsu | Sealing structure of spindle bolt, and gas turbine |
EP1758429A1 (en) * | 2005-08-26 | 2007-02-28 | Snecma | Heating device for a cylindrical part and use thereof in the assembly of an inter-axle bearing for a multi-stage turbine machine |
FR2889981A1 (en) * | 2005-08-26 | 2007-03-02 | Snecma | DEVICE FOR HEATING A CYLINDRICAL PIECE, USE IN THE ASSEMBLY OF AN INTER-TREE BEARING IN A TURBOMACHINE. |
US20070107306A1 (en) * | 2005-08-26 | 2007-05-17 | Snecma | Device for heating a cylindrical component and use in assembling an inter-shaft bearing in a turbomachine |
US7989733B2 (en) | 2005-08-26 | 2011-08-02 | Snecma | Device for heating a cylindrical component and use in assembling an inter-shaft bearing in a turbomachine |
US8476557B2 (en) | 2005-08-26 | 2013-07-02 | Snecma | Device for heating a cylindrical component and use in assembling an inter-shaft bearing in a turbomachine |
WO2008110429A1 (en) * | 2007-03-12 | 2008-09-18 | Siemens Aktiengesellschaft | Rotor of a gas turbine |
US8641365B2 (en) * | 2007-03-12 | 2014-02-04 | Siemens Aktiengesellschaft | Rotor of a gas turbine |
US20100166559A1 (en) * | 2007-03-12 | 2010-07-01 | Guido Ahaus | Rotor of a gas turbine |
US20100143149A1 (en) * | 2007-03-12 | 2010-06-10 | Francois Benkler | Turbine with at least one rotor which comprises rotor disks and a tie-bolt |
EP1970530A1 (en) * | 2007-03-12 | 2008-09-17 | Siemens Aktiengesellschaft | Rotor of a thermal fluid flow engine and fluid flow engine |
US8506239B2 (en) * | 2007-03-12 | 2013-08-13 | Siemens Aktiengesellschaft | Turbine with at least one rotor which comprises rotor disks and a tie-bolt |
CN101631932B (en) * | 2007-03-12 | 2013-01-16 | 西门子公司 | Rotor of a gas turbine |
US20100290911A1 (en) * | 2008-03-26 | 2010-11-18 | Man Diesel & Turbo Se | Turbine Rotor for a Gas Turbine |
US8727718B2 (en) | 2008-03-26 | 2014-05-20 | Man Diesel & Turbo Se | Turbine rotor for a gas turbine |
US20100158699A1 (en) * | 2008-12-22 | 2010-06-24 | Jerzy Makuszewski | Rotor mounting system for gas turbine engine |
US8100666B2 (en) | 2008-12-22 | 2012-01-24 | Pratt & Whitney Canada Corp. | Rotor mounting system for gas turbine engine |
US9810230B2 (en) | 2009-05-08 | 2017-11-07 | Nuovo Pignone Srl | Impeller for a turbomachine and method for attaching a shroud to an impeller |
US9816518B2 (en) | 2009-11-23 | 2017-11-14 | Massimo Giannozzi | Centrifugal impeller and turbomachine |
US9810235B2 (en) | 2009-11-23 | 2017-11-07 | Massimo Giannozzi | Mold for a centrifugal impeller, mold inserts and method for building a centrifugal impeller |
US9797255B2 (en) | 2011-12-14 | 2017-10-24 | Nuovo Pignone S.P.A. | Rotary machine including a machine rotor with a composite impeller portion and a metal shaft portion |
CN104870824A (en) * | 2012-12-19 | 2015-08-26 | 西门子公司 | Seal of a compressor rotor |
CN104870824B (en) * | 2012-12-19 | 2017-05-24 | 西门子公司 | Seal of a compressor rotor |
WO2014096036A1 (en) * | 2012-12-19 | 2014-06-26 | Siemens Aktiengesellschaft | Seal of a compressor rotor |
US9863426B2 (en) | 2012-12-19 | 2018-01-09 | Siemens Aktiengesellschaft | Seal of a compressor rotor |
RU2643269C2 (en) * | 2012-12-19 | 2018-01-31 | Сименс Акциенгезелльшафт | Compressor rotor seal |
US10174618B2 (en) | 2013-07-04 | 2019-01-08 | Siemens Aktiengesellschaft | Rotor for a turbine |
US20160130948A1 (en) * | 2013-07-04 | 2016-05-12 | Siemens Aktiengesellschaft | Rotor for a turbine |
US11162505B2 (en) | 2013-12-17 | 2021-11-02 | Nuovo Pignone Srl | Impeller with protection elements and centrifugal compressor |
CN104389644A (en) * | 2014-11-15 | 2015-03-04 | 哈尔滨广瀚燃气轮机有限公司 | Sealing structure for novel turbine motor torsion bearing rotor |
CN107023321A (en) * | 2017-05-31 | 2017-08-08 | 深圳智慧能源技术有限公司 | The centering torsion pass of multistage high speed turbine machine is locked mechanism |
US20240026789A1 (en) * | 2020-09-03 | 2024-01-25 | Siemens Energy Global GmbH & Co. KG | Rotor assembly for a gas turbine |
US12037919B2 (en) * | 2020-09-03 | 2024-07-16 | Siemens Energy Global GmbH & Co. KG | Rotor assembly for a gas turbine |
IT202100010781A1 (en) * | 2021-04-28 | 2022-10-28 | Nuovo Pignone Tecnologie Srl | ROTOR OF TURBO MACHINE WITH STACKED IMPELLERS AND TURBO MACHINE |
WO2022228727A1 (en) * | 2021-04-28 | 2022-11-03 | Nuovo Pignone Tecnologie - S.R.L. | Turbomachine rotor with stacked impellers and turbomachine |
AU2022266952B2 (en) * | 2021-04-28 | 2023-12-21 | Nuovo Pignone Tecnologie - S.R.L. | Turbomachine rotor with stacked impellers and turbomachine |
Also Published As
Publication number | Publication date |
---|---|
DE2135088A1 (en) | 1972-04-13 |
FR2111096A5 (en) | 1972-06-02 |
GB1296300A (en) | 1972-11-15 |
DE2135088B2 (en) | 1973-08-30 |
JPS5036683B1 (en) | 1975-11-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3680979A (en) | Rotor structure for turbo machines | |
US3356339A (en) | Turbine rotor | |
US3749516A (en) | Rotor structure for turbo machines | |
US3814539A (en) | Rotor sealing arrangement for an axial flow fluid turbine | |
US3976399A (en) | Rotor of disc construction for single-shaft gas turbine | |
EP0202188B1 (en) | Two stage turbine rotor assembly | |
US3610772A (en) | Bladed rotor | |
US2660399A (en) | Composite multistage turbomachine rotor | |
US2654565A (en) | Construction of rotors for compressors and like machines | |
US2579745A (en) | Axial-flow compressor or turbine | |
US10100642B2 (en) | Low diameter turbine rotor clamping arrangement | |
US4784572A (en) | Circumferentially bonded rotor | |
JPH07109161B2 (en) | Turbine engine rotor | |
US3597109A (en) | Gas turbine engine axial flow multistage compressor | |
US3339833A (en) | Axial fluid flow machine such as a compressor or turbine | |
US3304052A (en) | Rotor structure for an elastic fluid utilizing machine | |
JP2002519564A (en) | Turbomachine rotor | |
JPS59141800A (en) | Sleeve for shrink-fitting rotary machine | |
US6572337B1 (en) | Turbine rotor torque transmission | |
US3184153A (en) | Rotor construction | |
US3146635A (en) | Rotor balancing sleeve | |
US3846044A (en) | Turbomachine assembly | |
US3799698A (en) | Rotors for gas turbine engines | |
US3059901A (en) | Rotor construction | |
US2908518A (en) | Centering device |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: ELLIOTT TURBOMACHINERY CO., INC., A CORP OF DELAWA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST. SUBJECT TO LICENSE RECITED.;ASSIGNOR:CARRIER CORPORATION, A CORP OF DEL.;REEL/FRAME:004499/0922 Effective date: 19851220 |
|
AS | Assignment |
Owner name: FIRST NATIONAL BANK OF CHICAGO, THE,ILLINOIS Free format text: LICENSE;ASSIGNOR:ELLIOT TURBOMACHINERY CO., INC.;REEL/FRAME:004940/0562 Effective date: 19871109 Owner name: FIRST NATIONAL BANK OF CHICAGO, THE, ONE FIRST NAT Free format text: LICENSE;ASSIGNOR:ELLIOT TURBOMACHINERY CO., INC.;REEL/FRAME:004940/0562 Effective date: 19871109 |