US3893787A - Centrifugal compressor boundary layer control - Google Patents

Centrifugal compressor boundary layer control Download PDF

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Publication number
US3893787A
US3893787A US451257A US45125774A US3893787A US 3893787 A US3893787 A US 3893787A US 451257 A US451257 A US 451257A US 45125774 A US45125774 A US 45125774A US 3893787 A US3893787 A US 3893787A
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United States
Prior art keywords
grooves
blades
shroud
inlet
outlet
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Expired - Lifetime
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US451257A
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Burton A Jones
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Raytheon Technologies Corp
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United Aircraft Corp
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    • 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
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel
    • 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
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • a primary object of this invention is to provide a high-work centrifugal compressor of good efficiency which will minimize flow energy losses due to shroud friction heating.
  • Another object of the invention is to produce a shroud-side flow profile at the impeller exit to provide good diffuser performance.
  • a further object of this invention is to relieve the local shroud-side adverse pressure gradient with a particular form of boundary layer control that stabilizes the shroud-side flow and improves the impeller exit flow profile and thereby increases the efficiency of the impeller/diffuser system.
  • Another object of the present invention is to equilibrate blade-to-blade pressure differences (circumferential flow nonuniformity) that tend to produce local time-dependent high adverse pressure gradients with respect to the tangential direction.
  • FIG. I is a longitudinal cross section of a centrifugal compressor.
  • FIG. 2 is an enlarged cross section taken along the line 22 of FIG. 1.
  • FIG. 3 is a chart showing a comparison of compressor efficiency with surge margin for a 6:l pressure ratio impeller.
  • FIG. 1 a centrifugal compressor 1 having an impeller 4 with blades 6 is shown with an inlet section 2, a stationary shroud 8 adjacent the blades 6, and a diffuser 10.
  • the impeller 4 is splined to a shaft 12, which may form part of a gas turbine engine and is fixed to the shaft by being bolted at its rearward side to an annular flange 14 which is shown integral with the shaft.
  • the forward end of the impeller 4 is bolted to another annular flange 16 which is fixed to a sleeve 18 mounted around the shaft 12.
  • Sleeve 18 can be fixed with respect to shaft I2 by any means desired.
  • a compressor of this type is shown and described in U.S. Pat. No. 3.420.435.
  • FIG. 2 shows one of the grooves 20.
  • Each groove 20 has a bottom surface 20a and a depth D. while adjacent grooves are separated by a land 22 which is the portion of the shroud wall which joins two grooves.
  • the side of the blade 6 facing the indicated direction X of impeller rotation is labeled with a plus to indicate high pressure; and the side of the blade 6 facing away from the direction of rotation is labeled with a minus sign to indicate low pressure.
  • the volume provided by the circumferential grooves 20 accommodates low energy flow adjacent the wall of the shroud 8.
  • Low energy air adjacent the wall of the shroud 8 is pumped into each groove 20 by the high pressure side of the blades 6.
  • the meridional and normal velocity components are reduced to zero. resulting in increased static pressure and tangential velocity of the air in the cavity.
  • This accommodation of low'energy air reduces the size of the boundary layer in the vicinity of the grooves.
  • An equilibrium flow of air into and out of the grooves is established by the relative high and low pressure sides of the blade.
  • the partially stagnated air in the groove is pumped out of the groove as a result of the pressure difference between the high pressure in the groove and the low pressure on the low pressure side of the blade. whereupon it mixes with the higher energy through flow and is carried downstream.
  • the circumferential communication provided by the plurality of grooves. circumferential flow nonuniformities are washed out thus attenuating time non steady pressure gradients.
  • grooves 20 are located near the point of incipient boundary layer separation on the surface of the stationary shroud 8. Conventional boundary layer calculation techniques are used to estimate this point. It will usually be found to occur where the surface of the shroud adjacent the flowpath turns abruptly toward the radial direction. The depth D and width W of each groove 20 should approximate the boundary layer displacement thickness calculated at the point of incipient separation. If the depth or width of a groove 20 exceeds the boundary layer displacement thickness by a value greater than 2. the groove volume will accommodate higher energy air and the cf fectiveness will diminish. This observa'ion has been established from systematic experimentation with groove geometry. The optimum number of grooves and their spacing has also been established on the basis of systematic tests of a variety of grooved shroud configurations.
  • the optimum number of grooves was found to be no less than 4 and no more than 8.
  • the grooves were spaced one-half groove width apart. This means that the width of the land 22 is one-half of the width of the grooves. Where the side walls of the grooves are tapered the average groove width is used.
  • FIG. 3 is a comparison of net efficiency with surge margin for a 6:1 pressure ratio impeller with various shroud configurations.
  • the shroud configurations which were used involved a shroud having a smooth inner surface, a grooved inner surface having 4 grooves. and a grooved inner surface having 8 grooves.
  • a centrifugal compressor being mounted for rotation having an axial inlet for delivering a fluid thereto. and a radial outlet for receiving a compressed fluid therefrom, said compressor having blades thereon each blade having a continuous outer free edge from said inlet to said outlet. said blades having an abrupt flow path section from axial flow to radial flow, a fixed shroud located between said inlet and outlet spaced from the edges of said blades, said shroud having annular grooves located therearound facing said blades. said circumferential grooves being located on the surface of the shroud opposite the abrupt flow path section where the flowpath from said inlet turns abruptly toward a ratdial direction into said outlet.

Abstract

A centrifugal compressor is shown with an inlet directing a fluid thereto and a diffuser into which the compressor directs its output. A group or array of circumferential grooves are located in the surface of a stationary shroud which covers the blades of the compressor.

Description

United States Patent 1 [111 3,893,787
[451 July 8,1975
Jones [54] CENTRIFUGAL CQMPRESSOR BOUNDARY 963,540 H1950 France 4|5/2I3 R LAYER CONTROL I,O57,I37 5/1959 Germany 4l5/2l3 R [75] Inventor: Burton A. Jones, North Palm Beach,
Primary ExaminerI-Ienry F. Raduazo [73] Assignee: United Aircraft Corporation, East n y, g or mk r hy Hartford, Conn.
[22] Filed: Mar. 14, 1974 [2!] App]. N0.: 451,257 [57] ABSTRACT [52] U.S. CI 415/213 R; 4l5/DIG. 1; 415/215 A centrifugal compressor is shown with an inlet direct- (51] Int. Cl. F04D 7/02 ng a fl i hereto nd a diffuser into which the com- [58] Field of Search 415/213, 215, DIG. I; p es-S0 directs its output. A group or array of circum- 416/183, 186, 185 ferential grooves are located in the surface of a stationary shroud which covers the blades of the com- [56] References Cited pressor.
FOREIGN PATENTS OR APPLICATIONS 503,332 5/!954 Canada 415/213 R 3 Claims, 3 Drawing Figures 1 CENTRIFUGAL COMPRESSOR BOUNDARY LAYER CONTROL BACKGROUND OF THE INVENTION This invention relates to means for increasing compressor performance and one means previously used in the prior art has been to incorporate bleed openings for obtaining a desired flow characteristic.
SUMMARY OF THE INVENTION A primary object of this invention is to provide a high-work centrifugal compressor of good efficiency which will minimize flow energy losses due to shroud friction heating.
It is an object of this invention to reduce local adverse pressure gradients caused in a flowpath when the flow turns from an axial direction to a radial direction.
Another object of the invention is to produce a shroud-side flow profile at the impeller exit to provide good diffuser performance.
A further object of this invention is to relieve the local shroud-side adverse pressure gradient with a particular form of boundary layer control that stabilizes the shroud-side flow and improves the impeller exit flow profile and thereby increases the efficiency of the impeller/diffuser system.
Another object of the present invention is to equilibrate blade-to-blade pressure differences (circumferential flow nonuniformity) that tend to produce local time-dependent high adverse pressure gradients with respect to the tangential direction.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. I is a longitudinal cross section of a centrifugal compressor.
FIG. 2 is an enlarged cross section taken along the line 22 of FIG. 1.
FIG. 3 is a chart showing a comparison of compressor efficiency with surge margin for a 6:l pressure ratio impeller.
DESCRIPTION OF THE PREFERRED EMBODIMENT Referring to FIG. 1 a centrifugal compressor 1 having an impeller 4 with blades 6 is shown with an inlet section 2, a stationary shroud 8 adjacent the blades 6, and a diffuser 10. The impeller 4 is splined to a shaft 12, which may form part of a gas turbine engine and is fixed to the shaft by being bolted at its rearward side to an annular flange 14 which is shown integral with the shaft. The forward end of the impeller 4 is bolted to another annular flange 16 which is fixed to a sleeve 18 mounted around the shaft 12. Sleeve 18 can be fixed with respect to shaft I2 by any means desired. A compressor of this type is shown and described in U.S. Pat. No. 3.420.435.
An array of circumferential grooves 20 are located in the surface of the stationary shroud 8 exposed to the flow path between the blades 6 and through the impeller 4. FIG. 2 shows one of the grooves 20. Each groove 20 has a bottom surface 20a and a depth D. while adjacent grooves are separated by a land 22 which is the portion of the shroud wall which joins two grooves. The side of the blade 6 facing the indicated direction X of impeller rotation is labeled with a plus to indicate high pressure; and the side of the blade 6 facing away from the direction of rotation is labeled with a minus sign to indicate low pressure. The volume provided by the circumferential grooves 20 accommodates low energy flow adjacent the wall of the shroud 8. Low energy air adjacent the wall of the shroud 8 is pumped into each groove 20 by the high pressure side of the blades 6. In the cavity the meridional and normal velocity components are reduced to zero. resulting in increased static pressure and tangential velocity of the air in the cavity. This accommodation of low'energy air reduces the size of the boundary layer in the vicinity of the grooves. An equilibrium flow of air into and out of the grooves is established by the relative high and low pressure sides of the blade. The partially stagnated air in the groove is pumped out of the groove as a result of the pressure difference between the high pressure in the groove and the low pressure on the low pressure side of the blade. whereupon it mixes with the higher energy through flow and is carried downstream. As a result of the circumferential communication provided by the plurality of grooves. circumferential flow nonuniformities are washed out thus attenuating time non steady pressure gradients.
For maximum effectiveness. grooves 20 are located near the point of incipient boundary layer separation on the surface of the stationary shroud 8. Conventional boundary layer calculation techniques are used to estimate this point. It will usually be found to occur where the surface of the shroud adjacent the flowpath turns abruptly toward the radial direction. The depth D and width W of each groove 20 should approximate the boundary layer displacement thickness calculated at the point of incipient separation. If the depth or width of a groove 20 exceeds the boundary layer displacement thickness by a value greater than 2. the groove volume will accommodate higher energy air and the cf fectiveness will diminish. This observa'ion has been established from systematic experimentation with groove geometry. The optimum number of grooves and their spacing has also been established on the basis of systematic tests of a variety of grooved shroud configurations. The optimum number of grooves was found to be no less than 4 and no more than 8. The grooves were spaced one-half groove width apart. this means that the width of the land 22 is one-half of the width of the grooves. Where the side walls of the grooves are tapered the average groove width is used.
FIG. 3 is a comparison of net efficiency with surge margin for a 6:1 pressure ratio impeller with various shroud configurations. The shroud configurations which were used involved a shroud having a smooth inner surface, a grooved inner surface having 4 grooves. and a grooved inner surface having 8 grooves.
I claim:
I. A centrifugal compressor being mounted for rotation having an axial inlet for delivering a fluid thereto. and a radial outlet for receiving a compressed fluid therefrom, said compressor having blades thereon each blade having a continuous outer free edge from said inlet to said outlet. said blades having an abrupt flow path section from axial flow to radial flow, a fixed shroud located between said inlet and outlet spaced from the edges of said blades, said shroud having annular grooves located therearound facing said blades. said circumferential grooves being located on the surface of the shroud opposite the abrupt flow path section where the flowpath from said inlet turns abruptly toward a ratdial direction into said outlet.
2. A combination as set forth in claim I wherein the number of grooves range from 4 to 8.
3. A combination set forth in claim 1 wherein the grooves are spaced one-half of a groove width apart.

Claims (3)

1. A centrifugal compressor being mounted for rotation having an axial inlet for delivering a fluid thereto, and a radial outlet for receiving a compressed fluid therefrom, said compressor having blades thereon each blade having a continuous outer free edge from said inlet to said outlet, said blades having an abrupt flow path section from axial flow to radial flow, a fixed shroud located between said inlet and outlet spaced from the edges of said blades, said shroud having annular grooves located therearound facing said blades, said circumferential grooves being located on the surface of the shroud opposite the abrupt flow path section where the flowpath from said inlet turns abruptly toward a radial direction into said outlet.
2. A combination as set forth in claim 1 wherein the number of grooves range from 4 to 8.
3. A combination as set forth in claim 1 wherein the grooves are spaced one-half of a groove width apart.
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Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4061188A (en) * 1975-01-24 1977-12-06 International Harvester Company Fan shroud structure
US4063848A (en) * 1976-03-24 1977-12-20 Caterpillar Tractor Co. Centrifugal compressor vaneless space casing treatment
US4212585A (en) * 1978-01-20 1980-07-15 Northern Research And Engineering Corporation Centrifugal compressor
US4248566A (en) * 1978-10-06 1981-02-03 General Motors Corporation Dual function compressor bleed
US4479755A (en) * 1982-04-22 1984-10-30 A/S Kongsberg Vapenfabrikk Compressor boundary layer bleeding system
FR2669687A1 (en) * 1984-06-19 1992-05-29 Rolls Royce Plc Axial-flow compressor
WO1994002742A1 (en) * 1992-07-20 1994-02-03 Allied-Signal Inc. Rotary compressor with stepped cover contour
EP0614014A1 (en) * 1993-03-04 1994-09-07 ABB Management AG Radial compressor with a flow stabilising casing
EP0754864A1 (en) * 1995-07-18 1997-01-22 Ebara Corporation Turbomachine
US6164911A (en) * 1998-11-13 2000-12-26 Pratt & Whitney Canada Corp. Low aspect ratio compressor casing treatment
EP1134427A1 (en) * 2000-03-17 2001-09-19 Hitachi, Ltd. Turbo machines
US6375416B1 (en) 1993-07-15 2002-04-23 Kevin J. Farrell Technique for reducing acoustic radiation in turbomachinery
US6699008B2 (en) 2001-06-15 2004-03-02 Concepts Eti, Inc. Flow stabilizing device
EP1553304A2 (en) * 2004-01-08 2005-07-13 Samsung Electronics Co., Ltd. Turbo compressor
US20050152775A1 (en) * 2004-01-14 2005-07-14 Concepts Eti, Inc. Secondary flow control system
US20060088412A1 (en) * 2004-10-27 2006-04-27 Barton Michael T Compressor including an enhanced vaned shroud
US20060275113A1 (en) * 2002-08-13 2006-12-07 Hua Chen Compressor
US20090232642A1 (en) * 2008-03-12 2009-09-17 Atte Anema Adjustable compressor bleed system and method
EP2171283A1 (en) * 2007-02-14 2010-04-07 BorgWarner, Inc. Compressor housing
US20130142662A1 (en) * 2010-08-26 2013-06-06 Borgwarner Inc. Exhaust-gas turbocharger component
US20150132121A1 (en) * 2013-11-14 2015-05-14 Hon Hai Precision Industry Co., Ltd. Fan
US20150176422A1 (en) * 2012-06-25 2015-06-25 Borgwarner Inc. Exhaust-gas turbocharger
EP2899407A1 (en) * 2014-01-27 2015-07-29 Pratt & Whitney Canada Corp. Centrifugal compressor with recirculation groove in its shroud
US9551225B2 (en) 2013-01-23 2017-01-24 Concepts Nrec, Llc Structures and methods for forcing coupling of flow fields of adjacent bladed elements of turbomachines, and turbomachines incorporating the same
US9845810B2 (en) 2014-06-24 2017-12-19 Concepts Nrec, Llc Flow control structures for turbomachines and methods of designing the same
US20180291920A1 (en) * 2015-05-15 2018-10-11 Nuovo Pignone Tecnologie Srl Centrifugal compressor impeller and compressor comprising said impeller
US10132331B2 (en) 2013-12-17 2018-11-20 Man Energy Solutions Se Radial compressor stage
US20220163047A1 (en) * 2020-11-24 2022-05-26 Nuovo Pignone Tecnologie - S.R.L. Cold spray reinforced impeller shroud
US11396888B1 (en) 2017-11-09 2022-07-26 Williams International Co., L.L.C. System and method for guiding compressible gas flowing through a duct
US11828188B2 (en) 2020-08-07 2023-11-28 Concepts Nrec, Llc Flow control structures for enhanced performance and turbomachines incorporating the same

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR963540A (en) * 1950-07-17
CA503332A (en) * 1954-05-25 Andermatt Carl Centrifugal pump
DE1057137B (en) * 1958-03-07 1959-05-14 Maschf Augsburg Nuernberg Ag Blade gap seal on centrifugal machines with impellers without a cover band or cover disk

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR963540A (en) * 1950-07-17
CA503332A (en) * 1954-05-25 Andermatt Carl Centrifugal pump
DE1057137B (en) * 1958-03-07 1959-05-14 Maschf Augsburg Nuernberg Ag Blade gap seal on centrifugal machines with impellers without a cover band or cover disk

Cited By (49)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4061188A (en) * 1975-01-24 1977-12-06 International Harvester Company Fan shroud structure
US4063848A (en) * 1976-03-24 1977-12-20 Caterpillar Tractor Co. Centrifugal compressor vaneless space casing treatment
US4212585A (en) * 1978-01-20 1980-07-15 Northern Research And Engineering Corporation Centrifugal compressor
US4248566A (en) * 1978-10-06 1981-02-03 General Motors Corporation Dual function compressor bleed
US4479755A (en) * 1982-04-22 1984-10-30 A/S Kongsberg Vapenfabrikk Compressor boundary layer bleeding system
FR2669687A1 (en) * 1984-06-19 1992-05-29 Rolls Royce Plc Axial-flow compressor
CN1045812C (en) * 1992-07-20 1999-10-20 联合信号股份有限公司 Rotary compressor with stepped cover contour
WO1994002742A1 (en) * 1992-07-20 1994-02-03 Allied-Signal Inc. Rotary compressor with stepped cover contour
US5304033A (en) * 1992-07-20 1994-04-19 Allied-Signal Inc. Rotary compressor with stepped cover contour
EP0614014A1 (en) * 1993-03-04 1994-09-07 ABB Management AG Radial compressor with a flow stabilising casing
US6375416B1 (en) 1993-07-15 2002-04-23 Kevin J. Farrell Technique for reducing acoustic radiation in turbomachinery
US5707206A (en) * 1995-07-18 1998-01-13 Ebara Corporation Turbomachine
EP0754864A1 (en) * 1995-07-18 1997-01-22 Ebara Corporation Turbomachine
US6164911A (en) * 1998-11-13 2000-12-26 Pratt & Whitney Canada Corp. Low aspect ratio compressor casing treatment
EP1134427A1 (en) * 2000-03-17 2001-09-19 Hitachi, Ltd. Turbo machines
US6699008B2 (en) 2001-06-15 2004-03-02 Concepts Eti, Inc. Flow stabilizing device
US8550775B2 (en) * 2002-08-13 2013-10-08 Honeywell International Inc. Compressor
US20060275113A1 (en) * 2002-08-13 2006-12-07 Hua Chen Compressor
US7338251B2 (en) * 2004-01-08 2008-03-04 Samsung Electronics Co., Ltd. Turbo compressor
EP1553304A2 (en) * 2004-01-08 2005-07-13 Samsung Electronics Co., Ltd. Turbo compressor
CN100363628C (en) * 2004-01-08 2008-01-23 三星电子株式会社 Turbo compressor
US20050152786A1 (en) * 2004-01-08 2005-07-14 Samsung Electronics Co., Ltd. Turbo compressor
EP1553304A3 (en) * 2004-01-08 2009-06-24 Samsung Electronics Co., Ltd. Turbo compressor
US20050152775A1 (en) * 2004-01-14 2005-07-14 Concepts Eti, Inc. Secondary flow control system
US7025557B2 (en) 2004-01-14 2006-04-11 Concepts Eti, Inc. Secondary flow control system
US20060088412A1 (en) * 2004-10-27 2006-04-27 Barton Michael T Compressor including an enhanced vaned shroud
US7189059B2 (en) 2004-10-27 2007-03-13 Honeywell International, Inc. Compressor including an enhanced vaned shroud
EP2171283A1 (en) * 2007-02-14 2010-04-07 BorgWarner, Inc. Compressor housing
US20100098532A1 (en) * 2007-02-14 2010-04-22 Borgwarner Inc. Compressor housing
EP2171283A4 (en) * 2007-02-14 2013-01-30 Borgwarner Inc Compressor housing
US8105012B2 (en) 2008-03-12 2012-01-31 Opra Technologies B.V. Adjustable compressor bleed system and method
US20090232642A1 (en) * 2008-03-12 2009-09-17 Atte Anema Adjustable compressor bleed system and method
US20130142662A1 (en) * 2010-08-26 2013-06-06 Borgwarner Inc. Exhaust-gas turbocharger component
US9404370B2 (en) * 2010-08-26 2016-08-02 Borgwarner Inc. Exhaust-gas turbocharger component with microstructured surface
US20150176422A1 (en) * 2012-06-25 2015-06-25 Borgwarner Inc. Exhaust-gas turbocharger
US10119411B2 (en) * 2012-06-25 2018-11-06 Borgwarner Inc. Exhaust-gas turbocharger
US9551225B2 (en) 2013-01-23 2017-01-24 Concepts Nrec, Llc Structures and methods for forcing coupling of flow fields of adjacent bladed elements of turbomachines, and turbomachines incorporating the same
US20150132121A1 (en) * 2013-11-14 2015-05-14 Hon Hai Precision Industry Co., Ltd. Fan
US10132331B2 (en) 2013-12-17 2018-11-20 Man Energy Solutions Se Radial compressor stage
US20150211545A1 (en) * 2014-01-27 2015-07-30 Pratt & Whitney Canada Corp. Shroud treatment for a centrifugal compressor
US9644639B2 (en) * 2014-01-27 2017-05-09 Pratt & Whitney Canada Corp. Shroud treatment for a centrifugal compressor
EP2899407A1 (en) * 2014-01-27 2015-07-29 Pratt & Whitney Canada Corp. Centrifugal compressor with recirculation groove in its shroud
US9845810B2 (en) 2014-06-24 2017-12-19 Concepts Nrec, Llc Flow control structures for turbomachines and methods of designing the same
US9970456B2 (en) 2014-06-24 2018-05-15 Concepts Nrec, Llc Flow control structures for turbomachines and methods of designing the same
US20180291920A1 (en) * 2015-05-15 2018-10-11 Nuovo Pignone Tecnologie Srl Centrifugal compressor impeller and compressor comprising said impeller
US11053951B2 (en) * 2015-05-15 2021-07-06 Nuovo Pignone Srl Centrifugal compressor impeller and compressor comprising said impeller
US11396888B1 (en) 2017-11-09 2022-07-26 Williams International Co., L.L.C. System and method for guiding compressible gas flowing through a duct
US11828188B2 (en) 2020-08-07 2023-11-28 Concepts Nrec, Llc Flow control structures for enhanced performance and turbomachines incorporating the same
US20220163047A1 (en) * 2020-11-24 2022-05-26 Nuovo Pignone Tecnologie - S.R.L. Cold spray reinforced impeller shroud

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