US2428330A - Assembly of multistage internalcombustion turbines embodying contrarotating bladed members - Google Patents
Assembly of multistage internalcombustion turbines embodying contrarotating bladed members Download PDFInfo
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- US2428330A US2428330A US517273A US51727344A US2428330A US 2428330 A US2428330 A US 2428330A US 517273 A US517273 A US 517273A US 51727344 A US51727344 A US 51727344A US 2428330 A US2428330 A US 2428330A
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- blades
- shell
- compressor
- turbine
- rows
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
Definitions
- My main object is to facilitate assembly of the parts.
- Figures 2, 3 and 4 are views mainly of one of the independent turbine and compressor sections, Figure 2 being a perspective view of the shell with the augmenter blades omitted and with one in-. dependent turbine and compressor section shown withdrawn, whilst Figure 3 is an axial view thereof and Figure 4 a fragmentary developed plan of the independent section.
- the burning gases, mixed with the diluent air entering through the holes, 39, are led from the tubular members [8 to a stationary row of blades l9 forming nozzles through which the gases pass at high speed to the first row 20 of turbine blades mounted on the shell 2
- the shell carries external augmenter blades 22 coacting with stationaryaugmenter blades 23.
- the next row of turbine blades l5a fast on the sleeve it rotates at high speed to drive the final portion of H the compressor, this row and the next row 24 (on the shell) being of the reaction type.
- the final independent rows 15 and the coacting blades 25 x are all of the aerofoil type.
- the plant illustrated is one in which the turbine II is disposed radially outwardly of the compressor l2, the flow through the latter being from the top to the bottom, i. e., from the jet end to the front.
- the compressor comprises stationary blade rows l3, l3 and rotary rows l4, l4, the latter rows being fast with independent turbine rows l5, l5 from which they are shielded by shrouds.
- the first independent turbine row l5a is mounted to revolve with a sleeve I6 carrying a plurality of compressor rows Ila coacting with stationary compressor rows i3a.
- the primary output of the compressor flows, as indicated by the arrows, around and into the combustion chamber 38, which may be or any suitable construction.
- the chamber 38 is annular in form, open at its radially inner surface to receive the primary air required for combustion and the injected fuel which issues in the
- the blades l5 are spaced from one another sufiiciently to allow of assembly into the shell through the larger (top in Figure 1) end thereof, the blades passing between the blades 25 fast with the shell.
- FIG. 4 shows at Mb some of the compressor blades strengthened to carry the centrifugal forces.
- is mainly of aluminium, the blades 25 being carried by ring sections 21 having end clearance from one another when cold, as indicated at 28 ( Figure 3), the portions 21 being riveted at 29 to aluminum ribs 30 with heat insulating material 3
- the shell can be made from steel in one piece with the turbine blades 25 permanently fixed in it, this being possible by the new way of assembly as a consequence of the wide spacing of the turbine blades. assembling and dismantling the shell without interl'ering with the balance, which is a very important point because of the relatively great weight of the shell.
- drive shaft for auxiliaries, pass- L ing through the hollow feed nozzle 34, the drive shaft carrying a, gear 35 which is driven from the compressor sleeve l6 through a compound pinion 36 and gear 31.
- an outer shell having inwardly-extending blade rows. and a member within said shell having coacting outwardly-extending blade rows, said shell and member being mounted for relative rotation, the
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Sept 30, 1
947- F. A. M. HEPPNER 2,428,330 ASSEIBLY OF IULTISTAGE INTERNAL-COIBUSTION TURBINES EIBODYING CONTRA-ROTATING BLADED HEIBBRS Filed Jan. s. 1944 a Sheets-Sheet 1 EWING) pt- 30, 1947- F. A. M. HEPPNER 2,428,330
ASSEIBLY 0F IULTISTAGB INTERNALrCOIBUSTION TURBINBS BIBQDYIHG' CONTRA-BUTATING BLADED IEIBERS I Filed Jan. 6, 1944 5 Sheets-Sheet 2* INVENTOK Zn 5 M M PF 1947. F. A. M; HEPPNER 2 42 LSSEIBLY 0F IULTISIAGE IIITBRm-COIBUSTIOK TURBIIBS HBODYIIG COHTRA-EOTATIHG BLAD mm Filed Jan. 6, 1944 3 Shasta-Sheet 3 Patented Sept. 30, 1947 ASSEMBLY COMBUSTION F MULTISTAGE INTERNAL-.
TURBINES EMBODYING CONTRABOTATING BLADED MEMBERS Fritz Albert Max Heppner, Leamington Spa, England, assignor to Armstrong Sidd ley Motors Limited, Coventry, England Application January 6, 1944, Serial No. 517,273 In Great Britain January 15, 1943 1 This invention relates to a multi-stage-interpal-combustion turbine plant, and particularly to a compound, internal-combustion, turbine plant for jet-propulsion purposes, the plant having a contra-rotating shell carrying externally jet-augmenter blades.
My main object is to facilitate assembly of the parts.
For an understanding of this and of other objects and advantages of the invention attention Claims. (Cl. (ill-35.6)
form of sprays l1 from suitable orifices in a hollow feed nozzle sleeve 34, and is provided with a plurality of elbow-shaped tubular members l8 which extend axially toward and deliver the prodnets of combustion to the inlet of the turbine. Each of the tubular members I8 is also provided with a plurality of holes 38 communicating with an annular space 411 to which the remainder of should be directed to the following description, in
which one arrangement, according to the invention, is described with reference to the accompanying diagrammatic drawings, in which- Figure 1 is a part-sectional elevation of a Jetpropulsion turbine plant; and
Figures 2, 3 and 4 are views mainly of one of the independent turbine and compressor sections, Figure 2 being a perspective view of the shell with the augmenter blades omitted and with one in-. dependent turbine and compressor section shown withdrawn, whilst Figure 3 is an axial view thereof and Figure 4 a fragmentary developed plan of the independent section.
According to the invention, there are outwardly-extending compressor and/or turbine blade rows on an inner member or members coacting with inwardly-extending blade rows on an outer member or members, and the blades in each row are arranged and spaced from one another so as to admit of axial assembly of the said inner and outer members after the blades have been secured in position. Consequently, the outer member (or the output of the compressor is delivered in the manner indicated at the lower left-hand portion of Figure 1. 1
The burning gases, mixed with the diluent air entering through the holes, 39, are led from the tubular members [8 to a stationary row of blades l9 forming nozzles through which the gases pass at high speed to the first row 20 of turbine blades mounted on the shell 2|, these blades being partly or wholly of the impulse type. (The shell carries external augmenter blades 22 coacting with stationaryaugmenter blades 23.) The next row of turbine blades l5a fast on the sleeve it rotates at high speed to drive the final portion of H the compressor, this row and the next row 24 (on the shell) being of the reaction type. The final independent rows 15 and the coacting blades 25 x are all of the aerofoil type.
members) need not be split, 1. e., it (or they) may be integrally formed.
Referring now to Figures 1 to 4, the plant illustrated is one in which the turbine II is disposed radially outwardly of the compressor l2, the flow through the latter being from the top to the bottom, i. e., from the jet end to the front. The compressor comprises stationary blade rows l3, l3 and rotary rows l4, l4, the latter rows being fast with independent turbine rows l5, l5 from which they are shielded by shrouds. The first independent turbine row l5a is mounted to revolve with a sleeve I6 carrying a plurality of compressor rows Ila coacting with stationary compressor rows i3a.
The primary output of the compressor flows, as indicated by the arrows, around and into the combustion chamber 38, which may be or any suitable construction. As shown, the chamber 38 is annular in form, open at its radially inner surface to receive the primary air required for combustion and the injected fuel which issues in the As will be seen from Figures 2, 3 and 4 the blades l5 are spaced from one another sufiiciently to allow of assembly into the shell through the larger (top in Figure 1) end thereof, the blades passing between the blades 25 fast with the shell.
As each disc It has only a single compressor row the power to drive it is small enough to allow wide spacing of the turbine blades without excessive lift figures on the turbine blades. In other words, the turbine blades in a row have only small deflections.
Figure 4 shows at Mb some of the compressor blades strengthened to carry the centrifugal forces.
Conveniently theshel1 2| is mainly of aluminium, the blades 25 being carried by ring sections 21 having end clearance from one another when cold, as indicated at 28 (Figure 3), the portions 21 being riveted at 29 to aluminum ribs 30 with heat insulating material 3| interposed. Alternatively, the shell can be made from steel in one piece with the turbine blades 25 permanently fixed in it, this being possible by the new way of assembly as a consequence of the wide spacing of the turbine blades. assembling and dismantling the shell without interl'ering with the balance, which is a very important point because of the relatively great weight of the shell.
This feature. also allows of- I, in a similar way the blade rows Ila are arranged so that they can be slid axially between the stationary blade rows l3a.
At 33 I shows; drive shaft, for auxiliaries, pass- L ing through the hollow feed nozzle 34, the drive shaft carrying a, gear 35 which is driven from the compressor sleeve l6 through a compound pinion 36 and gear 31.
. What I claim as my invention and desire to, secure by Letters Patent of the United States is" 1. In an internal-combustion turbine plant, a
rotating shell carrying inwardly-extending blade rows, coacting contra-rotating blade rows, and a plurality of compressor portions rotatably mounted within said shell, each of said contra-rotating blade rows being carried by and driving one of said compressor portions, the blades in said rows being spaced circumferentially and arranged so that said compressor portions can be inserted into said shell in an axial direction after said blades have been secured in position. V
2. In an internal-combustion turbine plant, a. rotating shell carrying inwardly-extending turbine blade rows, contra-rotating shrouds within coacting turbine blade row and also an inwardly-extending compressor blade row, and coasting stationary compressor blade rows, the blades in said rows being spaced clrcumferentially and arranged so that said shrouds can be inserted into said shell in an axial direction after said blades have been secured in position. 3. Apparatus as defined in claim 2, includin outwardly-extending jet-augmenter blade rows 4 tion with its blades passing between said stationary blades to bring said blade rows into 00- acting position.
4. In an internal-combustion turbine plant, a
rotating shell carrying inwardly-extendingturbine blade rows, a'support extending axially through said shell, contra-rotating shrouds within said shell each carrying an outwardly-extending coacting turbine blade row and also an inwardly-extending compressor ,blade row, said shroud rings being rotatably mounted on said support, and enacting stationary compressor blade rows mounted on said support between said rotatable compressor blade rows, the blades or said turbine blade rows being spaced circumferentially and arranged so that said shrouds can be inserted into said shell in an axial direction after said blades have been secured in position.
5. In an internal-combustion turbine plant, an outer shell having inwardly-extending blade rows. and a member within said shell having coacting outwardly-extending blade rows, said shell and member being mounted for relative rotation, the
. blades of said rows being spaced circumferentialsaid shell each carrying an outwardly-extending on said shell and coacting stationary jet-augmenter blade rows, the augmenter blades of said rows being spaced circumferentially and arranged ly and arranged so that said member may be moved axially into coacting position -within said shell with the blades secured in position on said shell and member.
FRITZ ALBERT MAX HEPPNER.
REFERENCES CITED The following references are of record in the- Number Name Date 710,884 Parsons Oct. 7, 1902 980,644 Knight Jan. 3, 1911 1,016,080 McCulloch Jan. 30, 1912 Roder May 20, 1930
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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GB2428330X | 1943-01-15 |
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US2428330A true US2428330A (en) | 1947-09-30 |
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US517273A Expired - Lifetime US2428330A (en) | 1943-01-15 | 1944-01-06 | Assembly of multistage internalcombustion turbines embodying contrarotating bladed members |
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Cited By (35)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2458037A (en) * | 1946-08-01 | 1949-01-04 | Continental Aviat & Engineerin | Fluid energy machine |
US2548975A (en) * | 1944-01-31 | 1951-04-17 | Power Jets Res & Dev Ltd | Internal-combustion turbine power plant with nested compressor and turbine |
US2600235A (en) * | 1946-02-25 | 1952-06-10 | Galliot Jules Andre Norbert | Gas turbine rotor cooling means |
US2630677A (en) * | 1947-01-20 | 1953-03-10 | Donald W Seifert | Axial flow jet motor with reversely rotating continuous combustion type combustion products generator and turbine |
US2639583A (en) * | 1947-06-25 | 1953-05-26 | Harry C Steele | Contrarotating gas turbine having a power turbine and a plurality of compressor-turbines in series |
US2646209A (en) * | 1948-05-21 | 1953-07-21 | Galliot Jules Andre Norbert | Turbine driven multistage compressor |
US2702985A (en) * | 1944-01-31 | 1955-03-01 | Power Jets Res & Dev Ltd | Gas turbine power plant with power take-off from rotatable guide blading |
US2714378A (en) * | 1951-10-06 | 1955-08-02 | Porta Products Corp | Air heating method |
US2721445A (en) * | 1949-12-22 | 1955-10-25 | James V Giliberty | Aircraft propulsion plant of the propeller-jet turbine type |
DE968370C (en) * | 1954-09-11 | 1958-02-06 | Henschel & Sohn G M B H | Gas turbine for smaller capacities |
US2933287A (en) * | 1956-05-28 | 1960-04-19 | Alfred M Caddell | Multiple stage turbine unit |
US2938705A (en) * | 1955-05-26 | 1960-05-31 | Curtiss Wright Corp | Lightweight compressor or turbine structure |
US3002675A (en) * | 1957-11-07 | 1961-10-03 | Power Jets Res & Dev Ltd | Blade elements for turbo machines |
US3117750A (en) * | 1961-12-07 | 1964-01-14 | Havilland Engine Co Ltd | Aircraft propulsion apparatus |
US3186166A (en) * | 1958-11-26 | 1965-06-01 | Daimler Benz Ag | Gas turbine drive unit |
US3210254A (en) * | 1961-02-10 | 1965-10-05 | Gen Dynamics Corp | Heat extraction system for a nuclear reactor |
US3255584A (en) * | 1962-08-18 | 1966-06-14 | Daimler Benz Ag | Two stage gas turbine propulsion jet unit with thrust diverting means |
US3255585A (en) * | 1964-02-12 | 1966-06-14 | Daimler Benz Ag | Two-stage gas turbine propulsion jet unit with thrust diverting means |
US3818695A (en) * | 1971-08-02 | 1974-06-25 | Rylewski Eugeniusz | Gas turbine |
US4707978A (en) * | 1984-09-05 | 1987-11-24 | Latimer N.V. | Flow energy conversion machine |
US4765135A (en) * | 1986-10-29 | 1988-08-23 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Gas turbine engine |
US4809498A (en) * | 1987-07-06 | 1989-03-07 | General Electric Company | Gas turbine engine |
US6397577B1 (en) * | 2001-04-02 | 2002-06-04 | The United States Of America As Represented By The Secretary Of The Air Force | Shaftless gas turbine engine spool |
US6591873B1 (en) * | 2001-11-21 | 2003-07-15 | Air Cruisers Company | Turbo fan aspirator |
WO2007120066A1 (en) * | 2006-04-14 | 2007-10-25 | Gennady Mikhailovich Morgunov | The bladed machine (versions) |
US20090068033A1 (en) * | 2007-02-06 | 2009-03-12 | Masatsugu Ishiba | Fan driven by tip turbine |
US8726635B1 (en) * | 2007-04-05 | 2014-05-20 | The United States Of America As Represented By The Secretary Of The Air Force | Gas turbine engine with dual compression rotor |
US20160237895A1 (en) * | 2015-02-13 | 2016-08-18 | United Technologies Corporation | Turbine engine with a turbo-compressor |
US9995216B1 (en) * | 2017-08-28 | 2018-06-12 | Mustafa Rez | Disc turbine engine |
US10125722B2 (en) | 2015-02-13 | 2018-11-13 | United Technologies Corporation | Turbine engine with a turbo-compressor |
US10337401B2 (en) | 2015-02-13 | 2019-07-02 | United Technologies Corporation | Turbine engine with a turbo-compressor |
US10344763B2 (en) | 2017-08-28 | 2019-07-09 | Mustafa Rez | Disc turbo charger |
WO2021096366A1 (en) * | 2019-11-11 | 2021-05-20 | Tns Teknologi | A gas turbine engine |
US20220243732A1 (en) * | 2019-09-30 | 2022-08-04 | Feizal Alli Gaffoor | A multi-stage rotor |
US20220268206A1 (en) * | 2021-02-23 | 2022-08-25 | Jianchao Shu | Shaft-less twin rotor turbomachinery and the applications |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US710884A (en) * | 1901-07-01 | 1902-10-07 | Charles Algernon Parsons | Turbo compressor and pump. |
US980644A (en) * | 1907-10-29 | 1911-01-03 | Joseph Knight | Turbine. |
US1016080A (en) * | 1910-12-07 | 1912-01-30 | Frederick L Mcculloch | Reversible steam-turbine. |
US1759817A (en) * | 1926-06-23 | 1930-05-20 | Roder Karl | Steam turbine |
-
1944
- 1944-01-06 US US517273A patent/US2428330A/en not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US710884A (en) * | 1901-07-01 | 1902-10-07 | Charles Algernon Parsons | Turbo compressor and pump. |
US980644A (en) * | 1907-10-29 | 1911-01-03 | Joseph Knight | Turbine. |
US1016080A (en) * | 1910-12-07 | 1912-01-30 | Frederick L Mcculloch | Reversible steam-turbine. |
US1759817A (en) * | 1926-06-23 | 1930-05-20 | Roder Karl | Steam turbine |
Cited By (40)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2548975A (en) * | 1944-01-31 | 1951-04-17 | Power Jets Res & Dev Ltd | Internal-combustion turbine power plant with nested compressor and turbine |
US2702985A (en) * | 1944-01-31 | 1955-03-01 | Power Jets Res & Dev Ltd | Gas turbine power plant with power take-off from rotatable guide blading |
US2600235A (en) * | 1946-02-25 | 1952-06-10 | Galliot Jules Andre Norbert | Gas turbine rotor cooling means |
US2458037A (en) * | 1946-08-01 | 1949-01-04 | Continental Aviat & Engineerin | Fluid energy machine |
US2630677A (en) * | 1947-01-20 | 1953-03-10 | Donald W Seifert | Axial flow jet motor with reversely rotating continuous combustion type combustion products generator and turbine |
US2639583A (en) * | 1947-06-25 | 1953-05-26 | Harry C Steele | Contrarotating gas turbine having a power turbine and a plurality of compressor-turbines in series |
US2646209A (en) * | 1948-05-21 | 1953-07-21 | Galliot Jules Andre Norbert | Turbine driven multistage compressor |
US2721445A (en) * | 1949-12-22 | 1955-10-25 | James V Giliberty | Aircraft propulsion plant of the propeller-jet turbine type |
US2714378A (en) * | 1951-10-06 | 1955-08-02 | Porta Products Corp | Air heating method |
DE968370C (en) * | 1954-09-11 | 1958-02-06 | Henschel & Sohn G M B H | Gas turbine for smaller capacities |
US2938705A (en) * | 1955-05-26 | 1960-05-31 | Curtiss Wright Corp | Lightweight compressor or turbine structure |
US2933287A (en) * | 1956-05-28 | 1960-04-19 | Alfred M Caddell | Multiple stage turbine unit |
US3002675A (en) * | 1957-11-07 | 1961-10-03 | Power Jets Res & Dev Ltd | Blade elements for turbo machines |
US3186166A (en) * | 1958-11-26 | 1965-06-01 | Daimler Benz Ag | Gas turbine drive unit |
US3210254A (en) * | 1961-02-10 | 1965-10-05 | Gen Dynamics Corp | Heat extraction system for a nuclear reactor |
US3117750A (en) * | 1961-12-07 | 1964-01-14 | Havilland Engine Co Ltd | Aircraft propulsion apparatus |
US3255584A (en) * | 1962-08-18 | 1966-06-14 | Daimler Benz Ag | Two stage gas turbine propulsion jet unit with thrust diverting means |
US3255585A (en) * | 1964-02-12 | 1966-06-14 | Daimler Benz Ag | Two-stage gas turbine propulsion jet unit with thrust diverting means |
US3818695A (en) * | 1971-08-02 | 1974-06-25 | Rylewski Eugeniusz | Gas turbine |
US4707978A (en) * | 1984-09-05 | 1987-11-24 | Latimer N.V. | Flow energy conversion machine |
US4765135A (en) * | 1986-10-29 | 1988-08-23 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Gas turbine engine |
US4809498A (en) * | 1987-07-06 | 1989-03-07 | General Electric Company | Gas turbine engine |
US6397577B1 (en) * | 2001-04-02 | 2002-06-04 | The United States Of America As Represented By The Secretary Of The Air Force | Shaftless gas turbine engine spool |
US6591873B1 (en) * | 2001-11-21 | 2003-07-15 | Air Cruisers Company | Turbo fan aspirator |
WO2007120066A1 (en) * | 2006-04-14 | 2007-10-25 | Gennady Mikhailovich Morgunov | The bladed machine (versions) |
EA014075B1 (en) * | 2006-04-14 | 2010-08-30 | Геннадий Михайлович МОРГУНОВ | The bladed machine (versions) |
US20090068033A1 (en) * | 2007-02-06 | 2009-03-12 | Masatsugu Ishiba | Fan driven by tip turbine |
US8177527B2 (en) * | 2007-02-06 | 2012-05-15 | Toyota Jidosha Kabushiki Kaisha | Fan driven by tip turbine |
US8726635B1 (en) * | 2007-04-05 | 2014-05-20 | The United States Of America As Represented By The Secretary Of The Air Force | Gas turbine engine with dual compression rotor |
US20160237895A1 (en) * | 2015-02-13 | 2016-08-18 | United Technologies Corporation | Turbine engine with a turbo-compressor |
US10041408B2 (en) * | 2015-02-13 | 2018-08-07 | United Technologies Corporation | Turbine engine with a turbo-compressor |
US10125722B2 (en) | 2015-02-13 | 2018-11-13 | United Technologies Corporation | Turbine engine with a turbo-compressor |
US10337401B2 (en) | 2015-02-13 | 2019-07-02 | United Technologies Corporation | Turbine engine with a turbo-compressor |
US9995216B1 (en) * | 2017-08-28 | 2018-06-12 | Mustafa Rez | Disc turbine engine |
US10344763B2 (en) | 2017-08-28 | 2019-07-09 | Mustafa Rez | Disc turbo charger |
US20220243732A1 (en) * | 2019-09-30 | 2022-08-04 | Feizal Alli Gaffoor | A multi-stage rotor |
US11732718B2 (en) * | 2019-09-30 | 2023-08-22 | Feizal Alli Gaffoor | Multi-stage rotor |
WO2021096366A1 (en) * | 2019-11-11 | 2021-05-20 | Tns Teknologi | A gas turbine engine |
US11859537B2 (en) | 2019-11-11 | 2024-01-02 | Tns Teknologi | Gas turbine engine |
US20220268206A1 (en) * | 2021-02-23 | 2022-08-25 | Jianchao Shu | Shaft-less twin rotor turbomachinery and the applications |
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