US3706510A - Pipe diffuser with auxiliary bleed system - Google Patents
Pipe diffuser with auxiliary bleed system Download PDFInfo
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- US3706510A US3706510A US168205A US3706510DA US3706510A US 3706510 A US3706510 A US 3706510A US 168205 A US168205 A US 168205A US 3706510D A US3706510D A US 3706510DA US 3706510 A US3706510 A US 3706510A
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- Prior art keywords
- diffuser
- passages
- bleed
- longitudinal axes
- flow
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Classifications
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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
- F04D29/40—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
- 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
- F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
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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
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
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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
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/023—Details or means for fluid extraction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
Definitions
- ABSTRACT [52] US. Cl. ..415/145, 415/207, 4l5/2l1 [51] Int. Cl. ..F01b, 25/00, F04d29/44
- the disclosure illustrates a P p diffuser having [58] Field of Search ..415/144, 145, I48, 207, 20s, basic flow Passages Sized to handle the Output q 415,186,211 ments of a centrifugal compressor without a bleed requirement.
- The'diffuser has a series of auxiliary [56] References Cited bleed passages intersecting the inlet portions of the pipe diffuser passages.
- the bleed passages are sized to UNITED STATES PATENTS handle a supplementary bleed flow requirement when 2,289,231 7/1942 Auger et a] ..4l5/2l l needed. 2,620,626 l2/1952 Lysholm ..4l5/207 5 Claims, 4 Drawing Figures 3,333,762 8/1967 Vrana ..4l5/207 WM a, 3 e In r' 2 k E3 24 25 l D 32 l l ⁇ l 2 22 PKTENTED 7 9 SHEET 1 0F 2 P ATENTEM B 19 I97? 3.
- the present invention relates to compressors and more particularly to centrifugal compressors.
- the pipe diffuser has been proposed for use with centrifugal compressors designed to discharge air at supersonic velocities.
- This type of diffuser is described in US. Pat. No. 3,333,762 in the name of J. C. Vrana.
- the pipe diffuser comprises a series of circular passages drilled in an annular member surrounding a centrifugal impeller.
- the passages are oriented so that they intersect adjacent the periphery of the impeller to produce a series of scalloped leading edges to the inlets of the passages.
- This permits greater stability in the handling of transonic and supersonic flow discharged from the impeller.
- the reason for this is that the scalloped leading edges conform better to the velocity distribution of the flow than a straight leading edge of a normal diffuser.
- the net result is a centrifugal compressor with an improved efficiency capability at higher pressure ratios.
- APU auxiliary power unit
- the output requirements of APUs range between several modes of operation which demand widely varying compressor performance. At one extreme the compressor bleed is closed and the APU engine produces maximum power output, for example, to drive an alternator. At the other extreme there is a no-load condition and a substantial amount of air is bled from the compressor for cabin pressurization and other uses. Differences in airflow requirements at these two operating conditions make it difficult to size the flow passages of the compressor and the diffuser to operate efficiently under the maximum power condition and the maximum bleed condition.
- the diffuser may choke when the maximum bleed flow is called for. This is because the flow through the diffuser is greater than the throat area can handle at the chocking condition. This choking of the diffuser causes high losses and poor efficiency for operation in bleed mode.
- a pipe diffuser having flow passages intersecting to form scalloped inlet edges receiving flow from a centrifugal impeller.
- a series of auxiliary bleed passages extend from the diffuser passages to receive a portion of the air stream flowing through the diffuser.
- a means is provided to selectively permit or block flow through the bleed passages so that the effective throat area of the diffuser is varied.
- FIG. 1 is a sectional fragmentary view of a centrifugal compressor embodying the present invention
- FIG. 2 is a view of the diffuser of FIG. 1 taken on line 2-2 of FIG. 1; v
- FIG. 3 is an alternate embodiment of the compressor diffuser shown in FIGS. 1 and 2;
- FIG. 4 is a compressor MAP for the centrifugal compressor of FIG. 1.
- FIG. 1 there is shown a centrifugal compressor, generally indicated by reference character 10, which incorporates a rotatable impeller 12 having a series of radial blades 14.
- An annular diffuser housing 16 has an inner diameter 20 closely adjacent the periphery 18 of impeller 12.
- a series of generally tangentially directed diffuser passageways 22 are formed around the periphery of diffuser housing 16. These passages each comprise inlet portions 24, a throat section 25 and a conical outlet portion 26.
- the longitudinal axes D of the passages 22 are oriented so that they are all tangent to a reference circle, herein shown as the periphery 18 of impeller 12.
- the inlet portions 24 of passages 22 intersect to form a series of scalloped shaped entrance edges 30, as particularly shown in FIG. 2.
- a series of bleed passages 32 are formed in the diffuser housing 16 adjacent the diffuser passages 22.
- the passages 32 each comprise an inlet portion 34, a throat 35 and a generally conical outlet portion 36.
- the inlet portions 34 intersect the inlet portions 24 of passages 22 to form elliptically shaped inlets 38 (see FIG. 2).
- the outlet portions of the passages 32 connect through branch conduits 40 to a bleed manifold 42 having a suitably actuated flow control valve 44 in an overboard supply conduit 46.
- the axes D of passages 22 and axes B of passages 32 intersect at an angle 0 which is large enough to permit a separate bleed flow collecting conduit arrangement around the periphery of diffuser housing 16. However, 0 is small enough so that the static pressure recovery in the auxiliary bleed passages 32 are of the same order as those of the main passages 22.
- the impeller 12 rotates at a high rate of speed which causes air to be discharged generally tangentially from the tips of blades 14 at a high velocity.
- the air thus discharged enters the diffuser passages 22 where it is de-accelerated to a subsonic level in the inlet portions 24 for passage through throats 25 and subsonic diffusion in the outlet portions 26.
- the flow areas of throats 25 are sized to provide an effective flow in impeller 12 for a no-bleed condition that permits a maximum efficiency.
- the compressor operating line C is as shown in relation to the surge line of the compressor. This line is at a relatively high level of efficiency, as seen by the constant speed operating line C,. It should be noted that the compressor operates well upon the horizontal portion of line C, so that it is away from a choked condition.
- valve 44 is opened, thus permitting flow into bleed passages 32.
- the flow areas of passages 32 are sized to efficiently handle the bleed open requirements of the compressor 10. This increases the effective throat area of the diffuser and thereby moves the operating lines to line and the constant speed line to 0, on FIG. 4.
- the compressor still operates at an efficient level well away from a choked condition. As a result, the compressor efficiently handles a wide range of flow rates without the need for complicated and expensive variable passage geometry.
- valve 44 When bleed is no longer called for, valve 44 is closed to block off passages 32 and the diffuser functions in a normal fashion.
- the bleed passages 32 may be positioned so that their center lines B lie in the same plane as the center lines D of the diffuser passages (see FIG. 2) or they may be positioned at an obtuse angle relative to this plane. This modification is shown in FIG. 3 where passages 32' have their longitudinal axes B positioned at angle with respect to the plane containing the longitudinal axes D' of passages 22. This permits an axial shifting of the outlets of the two systems and reduces the mechanical interference between them.
- a compressor assembly as in claim 1 having predetermined flow requirements for bleed closed and bleed open conditions and wherein:
- said primary diffuser passageways have a flow area to provide maximum efficiency for a bleed closed condition; said auxiliary bleed passages have a flow area sized to provide maximum efficiency for a bleed open condition.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The disclosure illustrates a ''''pipe'''' diffuser having basic flow passages sized to handle the output requirements of a centrifugal compressor without a bleed requirement. The diffuser has a series of auxiliary bleed passages intersecting the inlet portions of the pipe diffuser passages. The bleed passages are sized to handle a supplementary bleed flow requirement when needed.
Description
Umted States Patent 51 3,706,510
4 OConnor [4 1 Dec. 19, 1972 54] PIPE DIFFUSER WITH AUXILIARY 3,420,435 H1969 Jarosz et al ...415/207 BLEED SYSTEM 3,604,818 9/1971 Cronstedt et al. ..415/207 [72] Inventor: J A- 9 3 195 5912;, Egan, FOREIGN PATENTS OR APPLICATIONS [73] Assignee: Avco Corporation, Stratford, Conn, 581,164 7/1933 Germany ..415/211 [22] Filed: 1971 7 Primary ExaminerHenry F. Raduazo [2]] App]. NO; 168,205 Attorney-Charles M. Hogan et al.
[57] ABSTRACT [52] US. Cl. ..415/145, 415/207, 4l5/2l1 [51] Int. Cl. ..F01b, 25/00, F04d29/44 The disclosure illustrates a P p diffuser having [58] Field of Search ..415/144, 145, I48, 207, 20s, basic flow Passages Sized to handle the Output q 415,186,211 ments of a centrifugal compressor without a bleed requirement. The'diffuser has a series of auxiliary [56] References Cited bleed passages intersecting the inlet portions of the pipe diffuser passages. The bleed passages are sized to UNITED STATES PATENTS handle a supplementary bleed flow requirement when 2,289,231 7/1942 Auger et a] ..4l5/2l l needed. 2,620,626 l2/1952 Lysholm ..4l5/207 5 Claims, 4 Drawing Figures 3,333,762 8/1967 Vrana ..4l5/207 WM a, 3 e In r' 2 k E3 24 25 l D 32 l l \l 2 22 PKTENTED 7 9 SHEET 1 0F 2 P ATENTEM B 19 I97? 3. 7 06510 sum 2 0F 2 L/ 30 V////////////////////l l OPER N INE BLE C ED SU LINE BL D CLOSED SURGE LINE BLEED OPEN CONSTA SP OPERA G L PRESSURE RATIO CORRECTED AIR FLOW (La/sec.)
INVENTOR. E JOHN A. o'c OR fiw m y ATTORNEYS.
PIPE DIFFUSER WITII AUXILIARY BLEED SYSTEM The present invention relates to compressors and more particularly to centrifugal compressors.
In recent years the so-called pipe diffuser has been proposed for use with centrifugal compressors designed to discharge air at supersonic velocities..This type of diffuser is described in US. Pat. No. 3,333,762 in the name of J. C. Vrana. Briefly, the pipe diffuser comprises a series of circular passages drilled in an annular member surrounding a centrifugal impeller. The passages are oriented so that they intersect adjacent the periphery of the impeller to produce a series of scalloped leading edges to the inlets of the passages. This permits greater stability in the handling of transonic and supersonic flow discharged from the impeller. The reason for this is that the scalloped leading edges conform better to the velocity distribution of the flow than a straight leading edge of a normal diffuser. The net result is a centrifugal compressor with an improved efficiency capability at higher pressure ratios. a
When such a diffuser is incorporated in a centrifugal compressor used in an auxiliary power unit (APU), certain problems may arise. Generally speaking, the output requirements of APUs range between several modes of operation which demand widely varying compressor performance. At one extreme the compressor bleed is closed and the APU engine produces maximum power output, for example, to drive an alternator. At the other extreme there is a no-load condition and a substantial amount of air is bled from the compressor for cabin pressurization and other uses. Differences in airflow requirements at these two operating conditions make it difficult to size the flow passages of the compressor and the diffuser to operate efficiently under the maximum power condition and the maximum bleed condition.
If the throat area of the diffuser is sized to provide adequate surge margin for the compressor at the maximum power output condition (minimum airflow), the diffuser may choke when the maximum bleed flow is called for. This is because the flow through the diffuser is greater than the throat area can handle at the chocking condition. This choking of the diffuser causes high losses and poor efficiency for operation in bleed mode.
Therefore it is an object of the present invention to provide a centrifugal compressor that operates at high efficiency over a wide range of pressure ratios and flow rates.
These ends are achieved by a pipe diffuser having flow passages intersecting to form scalloped inlet edges receiving flow from a centrifugal impeller. A series of auxiliary bleed passages extend from the diffuser passages to receive a portion of the air stream flowing through the diffuser. A means is provided to selectively permit or block flow through the bleed passages so that the effective throat area of the diffuser is varied.
The above and other related objects and features of the present invention will be apparent from a reading of the description of the disclosure shown in the accompanying drawings and the novelty thereof pointed out in the appended claims.
In the drawings:
FIG. 1 is a sectional fragmentary view of a centrifugal compressor embodying the present invention;
FIG. 2 is a view of the diffuser of FIG. 1 taken on line 2-2 of FIG. 1; v
FIG. 3 is an alternate embodiment of the compressor diffuser shown in FIGS. 1 and 2;
FIG. 4 is a compressor MAP for the centrifugal compressor of FIG. 1.
Referring to FIG. 1 there is shown a centrifugal compressor, generally indicated by reference character 10, which incorporates a rotatable impeller 12 having a series of radial blades 14. An annular diffuser housing 16 has an inner diameter 20 closely adjacent the periphery 18 of impeller 12. A series of generally tangentially directed diffuser passageways 22 are formed around the periphery of diffuser housing 16. These passages each comprise inlet portions 24, a throat section 25 and a conical outlet portion 26. The longitudinal axes D of the passages 22 are oriented so that they are all tangent to a reference circle, herein shown as the periphery 18 of impeller 12. The inlet portions 24 of passages 22 intersect to form a series of scalloped shaped entrance edges 30, as particularly shown in FIG. 2.
A series of bleed passages 32 are formed in the diffuser housing 16 adjacent the diffuser passages 22. The passages 32 each comprise an inlet portion 34, a throat 35 and a generally conical outlet portion 36. The inlet portions 34 intersect the inlet portions 24 of passages 22 to form elliptically shaped inlets 38 (see FIG. 2). The outlet portions of the passages 32 connect through branch conduits 40 to a bleed manifold 42 having a suitably actuated flow control valve 44 in an overboard supply conduit 46. As seen in FIG. 1, the axes D of passages 22 and axes B of passages 32 intersect at an angle 0 which is large enough to permit a separate bleed flow collecting conduit arrangement around the periphery of diffuser housing 16. However, 0 is small enough so that the static pressure recovery in the auxiliary bleed passages 32 are of the same order as those of the main passages 22.
During operation of the compressor 10 the impeller 12 rotates at a high rate of speed which causes air to be discharged generally tangentially from the tips of blades 14 at a high velocity. The air thus discharged enters the diffuser passages 22 where it is de-accelerated to a subsonic level in the inlet portions 24 for passage through throats 25 and subsonic diffusion in the outlet portions 26. The flow areas of throats 25 are sized to provide an effective flow in impeller 12 for a no-bleed condition that permits a maximum efficiency.
During this state, as shown on FIG. 4, the compressor operating line C is as shown in relation to the surge line of the compressor. This line is at a relatively high level of efficiency, as seen by the constant speed operating line C,. It should be noted that the compressor operates well upon the horizontal portion of line C, so that it is away from a choked condition.
In the absence of the bleed system comprising passages 32, a condition where air would be bled downstream of diffuser passages 22 causes the compressor to operate on the lower portion of line C, and into the choked region. This greatly lowers the overall efficiency of the compressor 10.
However, when the bleed flow is demanded for compressor 10, valve 44 is opened, thus permitting flow into bleed passages 32. The flow areas of passages 32 are sized to efficiently handle the bleed open requirements of the compressor 10. This increases the effective throat area of the diffuser and thereby moves the operating lines to line and the constant speed line to 0, on FIG. 4.
It can be seen that the compressor still operates at an efficient level well away from a choked condition. As a result, the compressor efficiently handles a wide range of flow rates without the need for complicated and expensive variable passage geometry.
When bleed is no longer called for, valve 44 is closed to block off passages 32 and the diffuser functions in a normal fashion.
The bleed passages 32 may be positioned so that their center lines B lie in the same plane as the center lines D of the diffuser passages (see FIG. 2) or they may be positioned at an obtuse angle relative to this plane. This modification is shown in FIG. 3 where passages 32' have their longitudinal axes B positioned at angle with respect to the plane containing the longitudinal axes D' of passages 22. This permits an axial shifting of the outlets of the two systems and reduces the mechanical interference between them.
While a preferred embodiment of the present invention has been described, it should be apparent to those skilled in the art that other modifications may be performed with equivalent results without departing from the spirit and scope of the present invention.
Having thus described the invention what is claimed as novel and desired to be secured by Letters Patent of primary diffuser passages intersecting adjacent the periphery of said impeller to form a series of generally scalloped inlet edges to said diffuser passages, said diffuser having a series of auxiliary bleed passages extending from said diffuser passages; the intersection between them being forward of the primary passage throat; and
means for selectively permitting or blocking flow through said bleed passages whereby the effective total throat area of said diffuser is varied.
2. A compressor assembly as in claim 1 wherein the longitudinal axes of the diffuser and bleed passages intersect at an angle sufficiently small so that the static pressure recovery potential in the secondary bleed passages is of the same order as in the primary passages.
3. A compressor assembly as in claim 1 having predetermined flow requirements for bleed closed and bleed open conditions and wherein:
said primary diffuser passageways have a flow area to provide maximum efficiency for a bleed closed condition; said auxiliary bleed passages have a flow area sized to provide maximum efficiency for a bleed open condition. 4. A compressor assembly as in claim 1 wherein the longitudinal axes of said diffuser passages substantially lie in a given plane and wherein the longitudinal axes of the bleed passages lie in the same plane and in between adgacent diffuser assages.
. A compress r assembly as in claim 1 wherein the longitudinal axes of said diffuser passages lie in a given plane and the longitudinal axes of said bleed passageways extend from said diffuser passageways at an oblique angle relative to said plane.
Claims (5)
1. A compressor assembly comprising: a rotatable bladed centrifugal impeller; an annular diffuser housing surrounding the periphery of said impeller, said diffuser housing having a plurality of generally tangentially directed primary diffuser passages intersecting adjacent the periphery of said impeller to form a series of generally scalloped inlet edges to said diffuser passages, said diffuser having a series of auxiliary bleed passages extending from said diffuser passages; the intersection between them being forward of the primary passage throat; and means for selectively permitting or blocking flow through said bleed passages whereby the effective total throat area of said diffuser is varied.
2. A compressor assembly as in claim 1 wherein the longitudinal axes of the diffuser and bleed passages intersect at an angle sufficiently small so that the static pressure recovery potential in the secondary bleed passages is of the same order as in the primary passages.
3. A compressor assembly as in claim 1 having predetermined flow requirements for bleed closed and bleed open conditions and wherein: said primary diffuser passageways have a flow area to provide maximum efficiency for a bleed closed condition; said auxiliary bleed passages have a flow area sized to provide maximum efficiency for a bleed open condition.
4. A compressor assembly as in claim 1 wherein the longitudinal axes of said diffuser passages substantially lie in a given plane and wherein the longitudinal axes of the bleed passages lie in the same plane and in between adjacent diffuser passages.
5. A compressor assembly as in claim 1 wherein the longitudinal axes of said diffuser passages lie in a given plane and the longitudinal axes of said bleed passageways extend from said diffuser passageways at an oblique angle relative to said plane.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US16820571A | 1971-08-02 | 1971-08-02 |
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US3706510A true US3706510A (en) | 1972-12-19 |
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---|---|---|---|
US168205A Expired - Lifetime US3706510A (en) | 1971-08-02 | 1971-08-02 | Pipe diffuser with auxiliary bleed system |
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Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3873231A (en) * | 1972-08-11 | 1975-03-25 | Allis Chalmers | Centrifugal pump diffuser |
US4022541A (en) * | 1976-04-12 | 1977-05-10 | General Motors Corporation | Assembled diffuser |
US4164845A (en) * | 1974-10-16 | 1979-08-21 | Avco Corporation | Rotary compressors |
US4182117A (en) * | 1978-01-09 | 1980-01-08 | Avco Corporation | Diffuser vane cusp bleed aperture with automatic ejector control device |
FR2443600A1 (en) * | 1978-11-20 | 1980-07-04 | Avco Corp | ROTARY COMPRESSORS |
US4251183A (en) * | 1978-01-30 | 1981-02-17 | The Garrett Corp. | Crossover duct assembly |
US4344737A (en) * | 1978-01-30 | 1982-08-17 | The Garrett Corporation | Crossover duct |
US4662817A (en) * | 1985-08-20 | 1987-05-05 | The Garrett Corporation | Apparatus and methods for preventing compressor surge |
US4948335A (en) * | 1988-12-30 | 1990-08-14 | Westinghouse Electric Corp. | Turbine moisture removal system |
US5236393A (en) * | 1991-08-28 | 1993-08-17 | Metal Industries, Inc. | Bypass damper in series-type ventilation fan |
US20100077768A1 (en) * | 2008-09-26 | 2010-04-01 | Andre Leblanc | Diffuser with enhanced surge margin |
US20130039748A1 (en) * | 2011-07-09 | 2013-02-14 | Ramgen Power Systems, Llc | Stator for supersonic compressor |
US9347380B2 (en) | 2012-12-28 | 2016-05-24 | General Electric Company | System and method for expanding a compressor bleed flow |
US9926942B2 (en) | 2015-10-27 | 2018-03-27 | Pratt & Whitney Canada Corp. | Diffuser pipe with vortex generators |
US10352237B2 (en) | 2016-05-26 | 2019-07-16 | Rolls-Royce Corporation | Diffuser having shaped vanes |
EP3608547A1 (en) * | 2018-08-10 | 2020-02-12 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes varying in natural vibration frequencies |
US10570925B2 (en) | 2015-10-27 | 2020-02-25 | Pratt & Whitney Canada Corp. | Diffuser pipe with splitter vane |
EP3647604A1 (en) * | 2018-10-31 | 2020-05-06 | Pratt & Whitney Canada Corp. | Diffuser with non-uniform throat areas |
US11098650B2 (en) | 2018-08-10 | 2021-08-24 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes having aero-dampers |
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DE581164C (en) * | 1933-07-22 | C H Jaeger & Co Pumpen U Gebla | Centrifugal machine, in particular centrifugal blower | |
US2289231A (en) * | 1940-01-18 | 1942-07-07 | Gen Electric | Centrifugal compressor |
US2620626A (en) * | 1944-09-01 | 1952-12-09 | Lysholm Alf | Gas turbine propulsion unit for aircraft |
US3333762A (en) * | 1966-11-16 | 1967-08-01 | United Aircraft Canada | Diffuser for centrifugal compressor |
US3420435A (en) * | 1967-02-09 | 1969-01-07 | United Aircraft Canada | Diffuser construction |
US3604818A (en) * | 1969-12-10 | 1971-09-14 | Avco Corp | Centrifugal compressor diffuser |
-
1971
- 1971-08-02 US US168205A patent/US3706510A/en not_active Expired - Lifetime
Patent Citations (6)
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DE581164C (en) * | 1933-07-22 | C H Jaeger & Co Pumpen U Gebla | Centrifugal machine, in particular centrifugal blower | |
US2289231A (en) * | 1940-01-18 | 1942-07-07 | Gen Electric | Centrifugal compressor |
US2620626A (en) * | 1944-09-01 | 1952-12-09 | Lysholm Alf | Gas turbine propulsion unit for aircraft |
US3333762A (en) * | 1966-11-16 | 1967-08-01 | United Aircraft Canada | Diffuser for centrifugal compressor |
US3420435A (en) * | 1967-02-09 | 1969-01-07 | United Aircraft Canada | Diffuser construction |
US3604818A (en) * | 1969-12-10 | 1971-09-14 | Avco Corp | Centrifugal compressor diffuser |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3873231A (en) * | 1972-08-11 | 1975-03-25 | Allis Chalmers | Centrifugal pump diffuser |
US4164845A (en) * | 1974-10-16 | 1979-08-21 | Avco Corporation | Rotary compressors |
US4022541A (en) * | 1976-04-12 | 1977-05-10 | General Motors Corporation | Assembled diffuser |
FR2456846A1 (en) * | 1978-01-09 | 1980-12-12 | Avco Corp | AIR INTAKE DEVICE ON TURBINE DIFFUSER WITH AUTOMATIC EJECTOR ADJUSTMENT |
US4182117A (en) * | 1978-01-09 | 1980-01-08 | Avco Corporation | Diffuser vane cusp bleed aperture with automatic ejector control device |
US4251183A (en) * | 1978-01-30 | 1981-02-17 | The Garrett Corp. | Crossover duct assembly |
US4344737A (en) * | 1978-01-30 | 1982-08-17 | The Garrett Corporation | Crossover duct |
FR2443600A1 (en) * | 1978-11-20 | 1980-07-04 | Avco Corp | ROTARY COMPRESSORS |
US4662817A (en) * | 1985-08-20 | 1987-05-05 | The Garrett Corporation | Apparatus and methods for preventing compressor surge |
US4948335A (en) * | 1988-12-30 | 1990-08-14 | Westinghouse Electric Corp. | Turbine moisture removal system |
US5236393A (en) * | 1991-08-28 | 1993-08-17 | Metal Industries, Inc. | Bypass damper in series-type ventilation fan |
US20100077768A1 (en) * | 2008-09-26 | 2010-04-01 | Andre Leblanc | Diffuser with enhanced surge margin |
US8235648B2 (en) | 2008-09-26 | 2012-08-07 | Pratt & Whitney Canada Corp. | Diffuser with enhanced surge margin |
US8556573B2 (en) | 2008-09-26 | 2013-10-15 | Pratt & Whitney Cananda Corp. | Diffuser with enhanced surge margin |
US20130164120A1 (en) * | 2011-07-09 | 2013-06-27 | Ramgen Power Systems, Llc | Supersonic compressor |
US20130039748A1 (en) * | 2011-07-09 | 2013-02-14 | Ramgen Power Systems, Llc | Stator for supersonic compressor |
US20130164121A1 (en) * | 2011-07-09 | 2013-06-27 | Ramgen Power Systems, Llc | Supersonic compressor |
US9347380B2 (en) | 2012-12-28 | 2016-05-24 | General Electric Company | System and method for expanding a compressor bleed flow |
US11215196B2 (en) | 2015-10-27 | 2022-01-04 | Pratt & Whitney Canada Corp. | Diffuser pipe with splitter vane |
US9926942B2 (en) | 2015-10-27 | 2018-03-27 | Pratt & Whitney Canada Corp. | Diffuser pipe with vortex generators |
US10502231B2 (en) | 2015-10-27 | 2019-12-10 | Pratt & Whitney Canada Corp. | Diffuser pipe with vortex generators |
US10570925B2 (en) | 2015-10-27 | 2020-02-25 | Pratt & Whitney Canada Corp. | Diffuser pipe with splitter vane |
US10352237B2 (en) | 2016-05-26 | 2019-07-16 | Rolls-Royce Corporation | Diffuser having shaped vanes |
EP3608547A1 (en) * | 2018-08-10 | 2020-02-12 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes varying in natural vibration frequencies |
US10823196B2 (en) | 2018-08-10 | 2020-11-03 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes varying in natural vibration frequencies |
US11098650B2 (en) | 2018-08-10 | 2021-08-24 | Pratt & Whitney Canada Corp. | Compressor diffuser with diffuser pipes having aero-dampers |
US10859096B2 (en) | 2018-10-31 | 2020-12-08 | Pratt & Whitney Canada Corp. | Diffuser with non-uniform throat areas |
EP3647604A1 (en) * | 2018-10-31 | 2020-05-06 | Pratt & Whitney Canada Corp. | Diffuser with non-uniform throat areas |
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