|Publication number||US3030006 A|
|Publication date||Apr 17, 1962|
|Filing date||May 27, 1958|
|Priority date||May 27, 1958|
|Publication number||US 3030006 A, US 3030006A, US-A-3030006, US3030006 A, US3030006A|
|Inventors||Shoup Jr Edgar C|
|Original Assignee||United Aircraft Corp|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (17), Referenced by (13), Classifications (5)|
|External Links: USPTO, USPTO Assignment, Espacenet|
April 1962 E. c. SHOUP, JR 3,030,006
CIRCUMFERENTIAL BLEED VALVE Filed May 27. 1958 2 Sheets-Sheet 1 F l G l IN VENTOR EDGAR C- SHOUF', JR.
BY ATTORNEY April 17, 1962 E. c. SHOUP, JR
CIRCUMFERENTIAL BLEED VALVE 2 Sheets-Sheet 2 Filed May 27. 1958 ATTORNEY United States Patent ()fiiice 3,03%,W Patented Apr. 17, 1962 3,030,006 tZRCUMFERENTIAL BLEED VALVE Edgm C. Shoup, Jr., Glastonbury, Conn, assignor to United Aircraft Corporation, East Hartford, Conn, a corporation of Delaware Filed May 27, 1958, Ser. No. 738,177 4 Claims. ((31. 230-414) This invention relates to a valve structure and is particularly adapted for a bleed valve for use in compressors such as an axial flow compressor used in connection with a gas turbine power plant.
Valves of this type must when in use allow a large volume of gas or air to bleed through when the valve is open but must be readily and quickly closed in order to discontinue the flow of air when bleeding of the compressor is no longer necessary. In order to obtain the desired large flow area, the valve is, in accordance with the present invention, in the form of a ring preferably as large in diameter as possible within the limitation of the machine with radially extending passages or ports which are closed by the movable valve or sleeve. Further in accordance with this invention, the valve is made to move axially uniformly in closing or opening the ports.
One of the principal features of the invention is a valve structure which will be easily operable, at the same time providing a substantially annular flow passage of large area.
Other features and advantages will be apparent from the specification and claims, and from the accompanying drawings which illustrate an embodiment of the invention.
FIG. 1 is a fragmentary sectional view of one stage of an axial fiow compressor showing the invention, the section being in part along the line 1-1 of FIG. 3.
PEG. 2 is a fragmentary view similar to FIG. 1 on a radial section spaced angularly from that of FIG. 1, this section being along the line 2-2 of FIG. 3.
FIG. 3 is a developed bottom view of a portion of the valve and the actuating system.
FIG. 4 is a cross-sectional view taken on line 4-4 of FIG. 1 of a portion of the ring and the actuating system.
FIG. 5 is a view of a detail substantially along the line 5-5 of FIG. 3.
The invention is shown as applied to an axial flow compressor having a row of stator vanes 2 the outer ends of which are supported from a casing 4 through a shroud ring 6 and the inner ends of which are carried by an inner shroud ring 8 attached to a housing or diaphragm 10. The housing is connected by radial struts 12 to a ring 14 forming an extension of the casing 4.
Downstream of the stator vanes 2 is a row of blades 16 carried by a rotor disc 18. The arrangement shows only a single stage in a multi-stage axial flow compressor of the type described in detail in the Savin Patent 2,747,367. The rotor disc 18 is connected through a plurality of axially extending botls 20 to an adjacent disc 22 and to an end bell 24 of the rotor. The latter is supported within the housing as by a bearing 26.
The invention is in a valve structure which controls the how of air from the space 28 surrounding the end bell 24 and the space 30 inside of the end bell. These spaces communicate through openings 31 in the end bell. The valve structure 32 is constructed to allow the flow of air into an annular space 34 formed between spaced shields 36 and 38 so that the air is discharged into the gas path of the compressor at a point adjacent the trailing edges of the stator vanes at their inner ends. The air enters the spaces 28 and 30 from the gas path at a point downstream of the row of blades 16 in a manner shown,
for example, in Baumann 2,418,801 and the valve of this application is thus comparable in function to the control valve of that patent.
The valve structure 32 includes a stationary valve base or housing 40 attached as by bolts 42 to the housing 10. A labyrinth seal 44 carried by the disc 18 engages an inner cylindrical portion of the valve housing 40 to close the space between the disc and the main housing 1.0. The valve housing 40 has a plurality of radially extending passages 46, the outer ends of which are normally closed by a valve sleeve 48 engaging with a cylindrical surface 50 on the valve housing 40 and having radial sealing surfaces 52 and 54 engaging respectively with cooperating surfaces 56 and 58 on the valve housing.
The valve sleeve 48 is moved axially in order to open radial passages 46 for the flow of air therethrough. ,To accomplish this, the sleeve 48 is connected to the valve housing 40 by a plurality of links 60 which are angularly spaced from one another and which, when the valvev sleeve is in closed position extend substantially axially as shown in FIG. 3. One end of each link is connected by a spherical joint 62 to a stud 64 on the sleeve and the other end of the link is connected by a spherical joint 66 to a stud 68 on the valve housing 40. With a plurality of angularly spaced links of this type connecting the housing to the sleeve, it will be apparent that a circumferential movement of the sleeve 48 will result in axial movement of the sleeve for uncovering the ports. This axial movement is uniform throughout the circumference of the sleeve by reason of the positioning of the several equally spaced parallel links 60.
The angular or circumferential movement of the sleeve is provided from a shaft 70 positioned axially within the housing 10 and having an actuating lever 72 at one end by which the rod may be turned, the other end of th shaft 70 carries an arm 74 substantially radially in alignment with the downstream edge of the sleeve 48. The outer end of this arm is connected through a pivotal joint 76 to a rod 78 which in turn is connected by another pivotal joint 80 to a pin 82, FIG. 5, on the sleeve 43. Thus rocking of the arm 72 by any suitable mechanism will cause circumferential movement of the sleeve resulting in axial movement of the sleeve for opening or closing of the ports.
It is to be understood that the invention is not limited to the specific embodiment herein illustrated and described but may be used in other ways without departure from its spirit as defined by the following claims.
1. A bleed valve for a compressor having a rotor with an axis about which it rotates, the bleed valve including a movable valve ring coaxial with the rotor, a valve housing cooperating with said ring, said housing having a plurality of openings therein arranged in a circumferentiaily extending row coaxial with the valve ring and adapted to be uncovered by said ring in response to axial movement of said ring, circumferentially spaced means for causing axial movement of the entire ring simultaneously, and said housing having sealing surfaces on axially opposite sides of the openings for engagement with said ring, each of said sealing surfaces being a radial surface on the housing for engagement with a cooperating radical surface of the ring.
2. A compressor having a row of stator vanes, a diaphragm radially inward of said vanes, a rotor adjacent to said diaphragm and having a row of blades thereon cooperating with the row of vanes, a valve base mounted on said diaphragm and having a row of openings therethrough, a seal element mounted on the rotor and having a cooperating sealing engagement with said valve base, a valve ring slidable on said base and adapted to movement into and out of a position covering said openings and means mounted on said diaphragm for moving said ring axially to cover or uncover said openings.
3. A compressor having a row of stator vanes, a diaphragm radially inward of said vanes, a rotor adjacent to said diaphragm and having a row of blades thereon cooperating with the roW of vanes, a valve base mounted on said diaphragm and having a TOW of openings therethrongh, a seal element mounted on the rotor and having a cooperating sealing engagement with said valve base, said base having a cylindrical portion, a valve ring axially slidable on said cylindrical portion and adapted to move into and out of a position covering said openings, an air passage from the inner ends of the stator vanes to said openings in the valve base, the inner ends of said openings communicating with the interior of the rotor.
4. A compressor having a row of stator vanes, a diaphragm extending inwardly from said vanes and a rotor adjacent to said diaphragm and having a row of blades thereon cooperating with the row of vanes, in combination with a valve housing mounted on said diaphragm and having a row of openings therein, a valve ring slidable on said housing and adapted by avial movement relative to said housing to uncover the row of openings therein, circumferentially spaced links, each link being pivotally connected to the housing at one end and to the ring at the other end for causing axial movement of the entire ring simultaneously, means connected to said ring for moving the ring circumferentially thereby causing a resultant axial movement greater than the action of the References Cited in the file of this patent UNITED STATES PATENTS 249,325 Edwards Nov. 8, 1881 552,396 Pyle Dec. 31, 1895 1,004,230 Balcorne Sept. 26, 1911 1,415,981 Bouche May 16, 1922 1,929,157 Waller Oct. 3, 1933 2,015,502 Trumpler Sept. 24, 1935 2,151,724 Wengel et al Mar. 28, 1939 2,308,679 Eason Jan. 19, 1943 2,418,801 Baumann Apr. 8, 1947 2,458,198 Poole Jan. 4, 1949 2,630,999 Lee Mar. 10, 1953 2,631,000 Lee Mar. 10, 1953 2,654,448 Benson Oct. 6, 1953 2,741,423 Lombard Apr. 10, 1956 2,819,836 Eberle Jan. 14, 1958 2,831,627 Brunner Apr. 22, 1958 FOREIGN PATENTS 879,280 Germany June 11, 1953
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US249325 *||Sep 27, 1881||Nov 8, 1881||edward s|
|US552396 *||Apr 11, 1895||Dec 31, 1895||F One||George c|
|US1004230 *||Nov 17, 1910||Sep 26, 1911||Holtzer Cabot Electric Co||Electric motor or generator.|
|US1415981 *||Feb 28, 1920||May 16, 1922||Gould Coupler Co||Governor|
|US1929157 *||Aug 24, 1932||Oct 3, 1933||Laval Steam Turbine Co||Turbine|
|US2015502 *||Sep 28, 1933||Sep 24, 1935||Ingersoll Rand Co||Blower|
|US2151724 *||Jan 12, 1937||Mar 28, 1939||Gordon Taylor Henry||Friction clutch|
|US2308679 *||Jun 19, 1939||Jan 19, 1943||Eason Clarence M||Clutch|
|US2418801 *||Jan 13, 1944||Apr 8, 1947||Vickers Electrical Co Ltd||Internal-combustion turbine plant|
|US2458198 *||Apr 15, 1944||Jan 4, 1949||United Aircraft Corp||Control for spill ports for freepiston units|
|US2630999 *||Feb 24, 1947||Mar 10, 1953||Baker Oil Tools Inc||Well casing cementing apparatus|
|US2631000 *||Feb 24, 1947||Mar 10, 1953||Baker Oil Tools Inc||Side ported well casing cementing collar|
|US2654448 *||Mar 20, 1948||Oct 6, 1953||Ary A Benson||Air-cooled brake|
|US2741423 *||Mar 7, 1952||Apr 10, 1956||Rolls Royce||Axial-flow compressors|
|US2819836 *||Oct 24, 1956||Jan 14, 1958||Oerlikon Engineering Company||Multi-stage radial compressor|
|US2831627 *||Jan 15, 1954||Apr 22, 1958||Westinghouse Electric Corp||Axial flow compressor apparatus|
|DE879280C *||Apr 16, 1940||Jun 11, 1953||Kuehnle Ag||Axialgeblaese oder Axialpumpe|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US3094270 *||Jul 27, 1959||Jun 18, 1963||Rolls Royce||Annular valve device|
|US3265000 *||Sep 3, 1963||Aug 9, 1966||Dowty Fuel Syst Ltd||Fluid metering device|
|US3638428 *||May 4, 1970||Feb 1, 1972||Gen Electric||Bypass valve mechanism|
|US3898799 *||Sep 27, 1973||Aug 12, 1975||Mtu Muenchen Gmbh||Device for bleeding-off compressor air in turbine jet engine|
|US4390318 *||Oct 8, 1980||Jun 28, 1983||Mtu Motoren-Und Turbinen-Union Muenche Gmbh||Apparatus for operating shut-off members in gas turbine engines, particularly in turbojet engines|
|US4827713 *||Jun 29, 1987||May 9, 1989||United Technologies Corporation||Stator valve assembly for a rotary machine|
|US6048171 *||Sep 9, 1997||Apr 11, 2000||United Technologies Corporation||Bleed valve system|
|US6755025||Jul 23, 2002||Jun 29, 2004||Pratt & Whitney Canada Corp.||Pneumatic compressor bleed valve|
|US9103283||Jun 20, 2012||Aug 11, 2015||United Technologies Corporation||Spherical-link end damper system with near constant engagement|
|US9328735||Sep 27, 2013||May 3, 2016||United Technologies Corporation||Split ring valve|
|EP0298015A2 *||Jun 28, 1988||Jan 4, 1989||United Technologies Corporation||Stator valve assembly for a rotary machine|
|WO1995010709A1 *||Oct 13, 1994||Apr 20, 1995||Pratt & Whitney Canada, Inc.||Axially opening cylindrical bleed valve|
|WO2004010004A1 *||Jul 8, 2003||Jan 29, 2004||Pratt & Whitney Canada Corp.||Pneumatic compressor bleed valve|
|U.S. Classification||415/145, 251/343|