US20160061219A1 - Radial compressor stage - Google Patents
Radial compressor stage Download PDFInfo
- Publication number
- US20160061219A1 US20160061219A1 US14/842,567 US201514842567A US2016061219A1 US 20160061219 A1 US20160061219 A1 US 20160061219A1 US 201514842567 A US201514842567 A US 201514842567A US 2016061219 A1 US2016061219 A1 US 2016061219A1
- Authority
- US
- United States
- Prior art keywords
- impeller
- stator
- flow
- diffuser
- guide blades
- 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.)
- Abandoned
Links
Images
Classifications
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
-
- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
-
- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
Definitions
- the invention relates to a radial compressor stage for a radial compressor.
- the or each radial compressor stage of a radial compressor comprises an impeller rotating with respect to a stator, wherein the impeller comprises a hub and multiple impeller blades on the rotor side.
- Each impeller blade of the impeller comprises a flow inlet edge and a flow outlet edge. Between the flow inlet edge and the flow outlet edge of each impeller blade a suction side, a pressure side, and an outer surface facing the stator extends.
- the outer surface of the respective impeller blade borders the stator and serves for sealing relative to the stator.
- Such an impeller of a radial compressor in which the outer surfaces of the impeller blades directly border the stator, does not comprise a shroud and is also called open impeller.
- the impeller blades are positioned in an impeller flow channel that is bounded by the hub of the impeller and the stator.
- the radial compressor stage comprises a diffuser positioned downstream of the impeller that comprises multiple guide blades on the stator side.
- Each guide blade of the diffuser has a flow inlet edge and a flow outlet edge. Between the flow inlet edge and the flow outlet edge of each guide blade a suction side and a pressure side extends.
- the guide blades are positioned in a diffuser flow channel bounded by the stator.
- a further radial compressor stage with such an impeller side gap is known from DE 10 2007 019 264 A1.
- the radial compressor stages are exposed to mechanical excitations and oscillations that can cause damage to the radial compressor stage, in particular to the impeller blades of the impeller of the radial compressor stage.
- mechanical excitations can be based on synchronous excitation mechanisms and on asynchronous excitation mechanisms.
- One embodiment of the present invention is based on creating a radial compressor stage for a radial compressor that fulfils the above requirements and accordingly is exposed to a low vibration excitation in particular through such asynchronous excitations.
- this object is solved through a radial compressor stage. Accordingly, the flow inlet edges of the guide blades of the diffuser on the stator side lie on a first circle contour namely in such a manner that the flow inlet edges of all guide blades on the stator side have an identical spacing from the flow inlet edges of the respective adjacent guide blades.
- the flow outlet edges of the guide blades of the diffuser on the stator side lie on a second circle contour, namely in such a manner that in at least one first circumferential position the flow outlet edge of the respective guide blade on the stator side has a spacing from the flow outlet edge of at least one adjacent guide blade other than in second circumferential positions.
- a radial compressor stage includes, at least one guide blade of the diffuser on the stator side that has a curvature which deviates from the other guide blades on the stator side.
- a radial compressor stage wherein, in at least one first circumferential position, a diffuser flow channel section formed between adjacent guide blades of the diffuser on the stator side has a flow cross section which deviates from the diffuser flow channel sections formed on second circumferential positions.
- asynchronous excitations of open impellers in radial compressors can be easily and reliably counteracted, as a result of which the vibration excitation in particular for the impeller blades of the impeller of the radial compressor stage can be reduced.
- FIG. 1 is a meridional section through a radial compressor stage according to the invention according to a first aspect of the invention
- FIG. 2 is an axial section through the radial compressor stage of FIG. 1 ;
- FIG. 3 is an axial section through a radial compressor stage according to a second aspect of the invention.
- FIG. 4 is a meridional section through a radial compressor stage according to the invention according to a third aspect of the invention.
- the present invention relates to a radial compressor with at least one radial compressor stage.
- FIG. 1 shows a detail of a radial compressor stage according to the invention in meridional section according to a first aspect of the invention
- FIG. 2 shows an axial section through the radial compressor stage of FIG. 1 .
- the radial compressor stage of FIG. 1 comprises an impeller 10 with multiple impeller blades 11 on the rotor side.
- the impeller 10 rotates relative to the stator 12 .
- the stator 12 can be a housing or a stator ring or the like.
- the impeller blades 11 are positioned in an impeller flow channel 13 bounded by a hub contour 14 on the rotor side and a stator contour 15 .
- Each impeller blade 12 comprises a flow inlet edge 16 and a flow outlet edge 17 . Between the flow inlet edge 16 and the flow outlet edge 17 of each impeller blade 11 a pressure side, a suction side and radially outside on the impeller blade 11 an outer surface 18 of the respective impeller blade 11 facing the stator 12 extends.
- the outer surface 18 of the impeller blade 11 borders the stator 12 and serves for sealing relative to the stator 12 .
- Such an impeller 10 in the case of which the outer surfaces 18 of the impeller blades 11 indirectly border the stator 12 does not have a shroud and is also called an open impeller.
- a diffuser 19 on the stator side is positioned downstream of the impeller 10 .
- the diffuser 19 comprises multiple guide blades 20 on the stator side.
- the guide blades 20 of the diffuser 19 on the stator side are positioned in a diffuser flow channel 21 bounded by the stator 12 .
- Each of the guide blades 20 of the diffuser 19 on the stator side comprises a flow inlet edge 22 and a flow outlet edge 23 . Between the flow inlet edge 22 and the flow outlet edge 23 of the respective guide blade 20 on the stator side a suction side 24 and a pressure side 25 of the respective guide blade extends.
- an intermediate flow channel 26 extends, via which medium compressed in the radial compressor stage starting out from the impeller 10 can flow in the direction of the diffuser 16 .
- a impeller side gap 28 is formed between a back side 27 of the impeller 10 and the stator 12 , wherein this impeller side gap 28 according to FIG. 1 is coupled to the intermediate flow channel 26 via a gap 34 .
- the invention relates to such details of a radial compressor stage with the help of which the danger of unsteady flow phenomena, which can lead to asynchronous excitation of the open impellers, can be reduced.
- all flow inlet edges 22 of all guide blades 20 of the diffuser 19 on the stator side lie on a first circle contour 29 .
- the flow inlet edges 22 of the guide blades 20 of the diffuser 19 on the stator side lie on the first circle contour 29 in such a manner that the flow inlet edges 22 of all guide blades 20 on the stator side have an identical spacing from the flow inlet edges 22 of the respective adjacent guide blades 20 .
- the flow inlet edges 22 of the guide blades 20 of the diffuser 19 located seen in circumferential direction of the diffuser flow channel 21 next to one another are accordingly evenly distributed seen in circumferential direction, so that accordingly all flow inlet edges 22 , which lie on the first circle contour 29 , have identical circumferential spacings to adjacent flow inlet edges 22 .
- the flow outlet edges 23 of the guide blades 20 of the diffuser 19 on the stator side lie on a second circle contour 30 .
- the flow outlet edges 23 of the guide blades 20 of the diffuser 19 on the stator side lie on the second circle contour 30 such that in at least one first circumferential position of the diffuser flow channel 21 the flow outlet edge 23 of the respective guide blade 20 on the stator side positioned there has a spacing from the flow outlet edge of at least one adjacent guide blade 20 other than in second circumferential positions of the diffuser flow channel 21 .
- the corresponding flow outlet edge 23 in a single circumferential position of the diffuser flow channel 21 has another spacing from the respective adjacent flow outlet edges 23 , that by contrast in the other circumferential positions the flow outlet edges 23 with respect to their circumferential positions are equally distributed.
- the respective guide blades 20 of the diffuser 19 on the stator side preferentially all have identical, second stepping angles.
- the guide blades 20 on the stator side positioned in the or each first circumferential position by contrast preferentially have a first stepping angle, which deviates from the second stepping angle, in particular by plus minus ⁇ 10°, preferably by plus minus ⁇ 7°, particularly preferably by ⁇ 5°, most preferably by ⁇ 3°.
- the first aspect and/or second aspect of the invention it is accordingly proposed for reducing the danger of unsteady flow phenomena, which can lead to an asynchronous excitation of the open impellers, to reposition the flow outlet edges 23 of selected guide blades 20 of the diffuser 19 on the stator side in circumferential direction, preferentially subject to cancelling or interrupting the flow outlet edges 23 which seen in circumferential direction of the diffuser flow channel 21 are otherwise equally distributed.
- the flow outlet edges 23 of all guide blades 20 of the diffuser 19 on the stator side can have different spacings from the respective adjacent flow outlet edges 23 .
- a flow outlet edge 23 ′′ (see dashed line course of the in FIG. 2 right guide blade) in the direction of the pressure side 25 of the respective adjacent guide blade 20 or a flow outlet edge 23 ′ (see dashed line course of the in FIG. 5 left guide blade) be relocated in circumferential direction in the direction of the suction side 24 of the respective adjacent guide blade 20 namely in such a manner that all flow outlet edges 23 as before still lie on the second circle contour.
- Those selected guide blades 20 which compared with the remaining guide blades 20 on the stator side, have a different stepping angle are characterized in that their stepping angle deviates in particular by ⁇ 10°, particularly preferably by ⁇ 5° from the stepping angles of the remaining guide blades 20 of the diffuser 19 .
- both the flow inlet edges 22 of the guide blades 20 of the diffuser 19 on the stator side positioned on the first circle contour 29 as well as the flow outlet edges 23 of the guide blades 20 of the diffuser 19 on the stator side positioned on the second circle contour 30 are equally distributed in circumferential direction, i.e. in each case have identical circumferential spacings.
- At least one guide blade 20 of the diffuser 19 on the stator side has a deviating curvature between the flow inlet edge 22 and the flow outlet edge 23 , namely a suction side 24 ′ and a pressure side 25 ′ with a curvature which deviates relative to the other guide blades 20 .
- first aspect of the invention and the second aspect of the invention combined with one another for reducing the risk of unsteady flow phenomena, which can lead to asynchronous excitation of the open impellers, on the radial compressor stage.
- a third aspect of the present invention is discussed in the following making reference to FIG. 4 .
- the third aspect of the invention it is proposed for reducing the risk of unsteady flow phenomena that can lead to asynchronous excitation of the open impellers, to change a diffuser flow channel section 33 formed between adjacent guide blades 20 of the diffuser 19 on the stator side in at least one first circumferential position of the diffuser flow channel 21 in such a manner that the same has a deviating flow cross section compared with the diffuser flow channel sections formed in second circumferential positions.
- the respective diffuser flow channel section 33 has a reduced flow cross section, namely because of the fact that the side walls 31 , 32 on the stator side bounding the respective diffuser flow channel section 33 , are curved towards the inside subject to reducing the flow cross section of the respective diffuser channel section 33 . It is pointed out that merely one of these side walls 31 , 32 bounding the respective diffuser flow channel 33 can be curved into the respective diffuser flow channel 33 . It is likewise possible, in selected circumferential positions, to expand the respective diffuser flow channel section with respect to its flow cross section, wherein at least one of these side walls 31 , 32 is then curved towards the outside into the stator 12 .
- the third aspect it is possible in a first extreme case that exclusively in a single circumferential position of the diffuser flow channel 21 the corresponding diffuser flow channel section 33 has a deviating flow cross section, that by contrast all other diffuser flow channel sections 33 have identical flow cross sections.
- the measures of the third aspect can be employed combined with the measures of the first aspect and/or the measures of the second aspect.
- the measures of the third aspect are employed on a radial compressor stage combined with the measures of the first aspect and with the measures of the second aspect.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102014012765.6 | 2014-09-02 | ||
DE102014012765.6A DE102014012765A1 (de) | 2014-09-02 | 2014-09-02 | Radialverdichterstufe |
Publications (1)
Publication Number | Publication Date |
---|---|
US20160061219A1 true US20160061219A1 (en) | 2016-03-03 |
Family
ID=53765155
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/842,567 Abandoned US20160061219A1 (en) | 2014-09-02 | 2015-09-01 | Radial compressor stage |
Country Status (7)
Country | Link |
---|---|
US (1) | US20160061219A1 (no) |
EP (1) | EP2993357B1 (no) |
JP (1) | JP6716220B2 (no) |
CN (1) | CN105387002B (no) |
DE (1) | DE102014012765A1 (no) |
NO (1) | NO3191511T3 (no) |
RU (1) | RU2691699C2 (no) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11098730B2 (en) | 2019-04-12 | 2021-08-24 | Rolls-Royce Corporation | Deswirler assembly for a centrifugal compressor |
US11187243B2 (en) | 2015-10-08 | 2021-11-30 | Rolls-Royce Deutschland Ltd & Co Kg | Diffusor for a radial compressor, radial compressor and turbo engine with radial compressor |
US11286952B2 (en) | 2020-07-14 | 2022-03-29 | Rolls-Royce Corporation | Diffusion system configured for use with centrifugal compressor |
US11441516B2 (en) * | 2020-07-14 | 2022-09-13 | Rolls-Royce North American Technologies Inc. | Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features |
US11578654B2 (en) | 2020-07-29 | 2023-02-14 | Rolls-Royce North American Technologies Inc. | Centrifical compressor assembly for a gas turbine engine |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR102427392B1 (ko) * | 2018-01-24 | 2022-07-29 | 한화에어로스페이스 주식회사 | 압축기용 디퓨저 |
EP3650709A1 (de) * | 2018-11-08 | 2020-05-13 | ABB Turbo Systems AG | Beschaufelte diffusoranordnung für einen radialverdichter |
EP3848590A1 (de) * | 2020-01-07 | 2021-07-14 | ABB Schweiz AG | Abströmbereich eines verdichters, verdichter mit einem solchen abströmbereich, und turbolader mit dem verdichter |
RU2757150C1 (ru) * | 2020-11-03 | 2021-10-11 | Акционерное общество "Интер РАО - Электрогенерация" | Осевой многоступенчатый компрессор с впрыском воды в его проточную часть |
CN113882971B (zh) * | 2021-09-15 | 2023-02-03 | 浙江理工大学 | 一种火箭发动机涡轮泵的定子导叶结构 |
Citations (9)
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US3289921A (en) * | 1965-10-08 | 1966-12-06 | Caterpillar Tractor Co | Vaneless diffuser |
US3658437A (en) * | 1970-03-27 | 1972-04-25 | Caterpillar Tractor Co | Diffuser including vaneless and vaned sections |
US4877373A (en) * | 1988-02-08 | 1989-10-31 | Dresser-Rand Company | Vaned diffuser with small straightening vanes |
US4900225A (en) * | 1989-03-08 | 1990-02-13 | Union Carbide Corporation | Centrifugal compressor having hybrid diffuser and excess area diffusing volute |
US5064344A (en) * | 1989-11-01 | 1991-11-12 | Sundstrand Corporation | Partial throat diffuser |
US5165849A (en) * | 1990-09-05 | 1992-11-24 | Hitachi, Ltd. | Centrifugal compressor |
JP2004100553A (ja) * | 2002-09-09 | 2004-04-02 | Mitsubishi Heavy Ind Ltd | 回転機械の静翼構造 |
US20080038114A1 (en) * | 2005-08-09 | 2008-02-14 | Ahmed Abdelwahab | Airfoil diffuser for a centrifugal compressor |
US20130309066A1 (en) * | 2012-05-16 | 2013-11-21 | Dyson Technology Limited | Fan |
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US3006603A (en) * | 1954-08-25 | 1961-10-31 | Gen Electric | Turbo-machine blade spacing with modulated pitch |
SU1525335A1 (ru) * | 1988-03-09 | 1989-11-30 | Университет дружбы народов им.Патриса Лумумбы | Лопаточный диффузор центробежного компрессора |
JP3110205B2 (ja) * | 1993-04-28 | 2000-11-20 | 株式会社日立製作所 | 遠心圧縮機及び羽根付ディフューザ |
DE19502808C2 (de) | 1995-01-30 | 1997-02-27 | Man B & W Diesel Ag | Radialströmungsmaschine |
JPH10176699A (ja) * | 1996-12-18 | 1998-06-30 | Ishikawajima Harima Heavy Ind Co Ltd | 遠心圧縮機 |
DE59809867D1 (de) * | 1998-05-25 | 2003-11-13 | Abb Turbo Systems Ag Baden | Radialverdichter |
EP1860325A1 (de) * | 2006-05-26 | 2007-11-28 | ABB Turbo Systems AG | Diffusor |
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DE102007034236A1 (de) * | 2007-07-23 | 2009-02-05 | Continental Automotive Gmbh | Radialverdichter mit einem Diffusor für den Einsatz bei einem Turbolader |
JP2009150308A (ja) * | 2007-12-20 | 2009-07-09 | Toyota Motor Corp | 遠心圧縮機 |
JP5665535B2 (ja) * | 2010-12-28 | 2015-02-04 | 三菱重工業株式会社 | 遠心圧縮機 |
RU2493439C1 (ru) * | 2012-02-17 | 2013-09-20 | Общество с ограниченной ответственностью Деловой центр "Галактика" | Центробежный насос |
CN103671270B (zh) * | 2013-11-30 | 2016-03-30 | 西安交通大学 | 一种扩压器叶片可振荡的离心压缩机 |
-
2014
- 2014-09-02 DE DE102014012765.6A patent/DE102014012765A1/de not_active Withdrawn
-
2015
- 2015-07-31 EP EP15179255.3A patent/EP2993357B1/de active Active
- 2015-08-31 JP JP2015170238A patent/JP6716220B2/ja active Active
- 2015-08-31 RU RU2015137073A patent/RU2691699C2/ru active
- 2015-09-01 US US14/842,567 patent/US20160061219A1/en not_active Abandoned
- 2015-09-02 CN CN201510553935.7A patent/CN105387002B/zh active Active
-
2016
- 2016-11-14 NO NO16798122A patent/NO3191511T3/no unknown
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US3289921A (en) * | 1965-10-08 | 1966-12-06 | Caterpillar Tractor Co | Vaneless diffuser |
US3658437A (en) * | 1970-03-27 | 1972-04-25 | Caterpillar Tractor Co | Diffuser including vaneless and vaned sections |
US4877373A (en) * | 1988-02-08 | 1989-10-31 | Dresser-Rand Company | Vaned diffuser with small straightening vanes |
US4900225A (en) * | 1989-03-08 | 1990-02-13 | Union Carbide Corporation | Centrifugal compressor having hybrid diffuser and excess area diffusing volute |
US5064344A (en) * | 1989-11-01 | 1991-11-12 | Sundstrand Corporation | Partial throat diffuser |
US5165849A (en) * | 1990-09-05 | 1992-11-24 | Hitachi, Ltd. | Centrifugal compressor |
JP2004100553A (ja) * | 2002-09-09 | 2004-04-02 | Mitsubishi Heavy Ind Ltd | 回転機械の静翼構造 |
US20080038114A1 (en) * | 2005-08-09 | 2008-02-14 | Ahmed Abdelwahab | Airfoil diffuser for a centrifugal compressor |
US20130309066A1 (en) * | 2012-05-16 | 2013-11-21 | Dyson Technology Limited | Fan |
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Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11187243B2 (en) | 2015-10-08 | 2021-11-30 | Rolls-Royce Deutschland Ltd & Co Kg | Diffusor for a radial compressor, radial compressor and turbo engine with radial compressor |
US11098730B2 (en) | 2019-04-12 | 2021-08-24 | Rolls-Royce Corporation | Deswirler assembly for a centrifugal compressor |
US11286952B2 (en) | 2020-07-14 | 2022-03-29 | Rolls-Royce Corporation | Diffusion system configured for use with centrifugal compressor |
US11441516B2 (en) * | 2020-07-14 | 2022-09-13 | Rolls-Royce North American Technologies Inc. | Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features |
US11815047B2 (en) | 2020-07-14 | 2023-11-14 | Rolls-Royce North American Technologies Inc. | Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features |
US11578654B2 (en) | 2020-07-29 | 2023-02-14 | Rolls-Royce North American Technologies Inc. | Centrifical compressor assembly for a gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
DE102014012765A1 (de) | 2016-03-03 |
EP2993357B1 (de) | 2018-02-21 |
JP6716220B2 (ja) | 2020-07-01 |
EP2993357A3 (de) | 2016-04-13 |
JP2016053363A (ja) | 2016-04-14 |
NO3191511T3 (no) | 2018-02-17 |
CN105387002A (zh) | 2016-03-09 |
RU2015137073A3 (no) | 2018-10-29 |
RU2015137073A (ru) | 2017-03-07 |
RU2691699C2 (ru) | 2019-06-17 |
EP2993357A2 (de) | 2016-03-09 |
CN105387002B (zh) | 2019-10-25 |
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