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Auxiliary Equipment

Auxiliary Equipment There is thus no need to pressurize the reservoir. unit is being produced by Vickers Incorporated, Auxiliary Equipment Oakman Boulevard, Detroit 32, Michigan. The unit consists of a two-stage pump driven b standard Vickers 3,000 lb./sq. in. hydraulic mot which is supplied from the main system. The Details of Some Components Used for stage of the booster pump is a centrifugal impel which is fed by gravity from the reservoir. The f Subsidiary Services in Aircraft is then passed on to the second stage, a vane pun from which it goes into the system supply line at to 100 lb./sq. in. The output of the unit ranges from 5 U.S. g New Lockheed Hydraulic Pump cylinder in such a position that it is partly uncovered min. at a differential pressure of 100 lb./sq. in. shortly before the plunger reaches the bottom of its 35 gal./min. at 18 lb./sq. in. differential. The weig A new enginc-driven hydraulic pump with a rated stroke. On the compression stroke the plunger covers is 9-1 lb. Depending on the motor size used delive maximum working pressure of 3,000 lb./sq. in., and a the inlet port and trapped fluid is forced through a is twenty-three to thirty-three times the fluid fl rated minimum delivery of 5-12 gal./min. has been passage leading from the top of the cylinder, past a through the driving hydraulic motor. announced by the Aircraft Division of the Lockheed delivery valve into an annular passage in the high- Hydraulic Brake Co. Ltd. pressure end cover leading to the outlet connexion. Gas Turbine-driven Generators This pump, which is known as the Mark 8, has The inlet passages on the new unit, however, have twice the output of the Mark 7, which, with a working The Solar Aircraft Company, San Diego 12, Ca been slightly re-designed, and the drive shaft has been pressure of 3,000 lb./sq. in. and a delivery rate of fornia, U.S.A., has introduced two airborne gcnerati modified and strengthened to meet the heavier de­ 2½ gal./min., was previously the largest-capacity sets powered by their Mars gas turbine, which d mand on it made by the higher output. pump made by Lockheed. livers over 40 h.p. One is an a.c./d.c. unit givi 'Non-flam' and other water-based fluids can be Work on the Mark 8 began when it became ap­ 8kva/14kw respectively, and the other a I4kw d used in hydraulic systems which are associated with parent that the demand for hydraulic power in some unit. They arc designed to operate at up to 20,000 the Mark 8 pump, and the shaft seals are resistant to of the larger aircraft of today and in types contem­ and over a temperature range of +130 deg. F. the synthetic turbine oils which are now becoming —65 deg. F. The starting system is automatic, an plated for the future would exceed the capacity of popular. the unit is protected with overspecd and ovcrheatin existing pumps. The following figures give a brief outline of the cut-outs. The arrangement of the circuit is shown Structurally, the new unit has many of the features performance of the Lockheed Mark 8 hydraulic FIG. 3. of the Mark 7, and might almost be described as a pump: 'double-banked Mark 7'. The Mark 7 is a seven- The turbine power unit consists of a ccntrifug Rated maximum working pressure, 3,000 lb./sq. in. cylinder radial plunger pump actuated by an eccentric compressor discharging to a single combustion cham Rated minimum delivery at 3,000 lb./sq. in. and ber. Burning gases are ducted to the radial inflo shaft which is integral with the driving shaft; the Mark 3,300 r.p.m., is 5-12 gal./min. single-stage turbine, which is mounted on the sam 8 has fourteen cylinders arranged in two radial banks, Approximate horse-power at the above speed and shaft as the compressor, and separated from it by and is actuated by a balanced two-throw eccentric pressure is 12-9. diaphragm. The shaft runs at 36,400 r.p.m. and this shaft. Because of the multiplicity of cylinders, the Rated maximum cruising speed, 3,300 r.p.m. reduced by a pair of spiral bevel gears to 4,500 an hydraulic system is free from the pressure pulses Overspecd at 3,000 lb./sq. in. 4,000 r.p.m. 6,000 r.p.m. The unit will run on high-octane gasoline which arc unavoidable when pumps with com­ paratively few cylinders arc employed. jet fuels or diescl oil, the fuel consumption being o the order of 3}-4 lb. per kw-hour. The weights a No attempt has been made to give the new pump Hydraulic Fluid Booster Pump 350 lb. for the a.c./d.c. set and 230 lb. for the d.c. set greater versatility than that of the Mark 7. It is, like The overhaul life is quoted as 500 hours, with a 60 the other, a straight-forward pumping unit with no An example of current American practice in hy­ hour routine service. off-loading devices or other features that might impair draulic equipment is illustrated in no. 2. It is a its efficiency or destroy its simplicity. It is also cool hydraulic booster pump which is mounted on the With its high fuel consumption the number o fluid reservoir, when the system pumps are at some applications for such a unit will be limited, but the running. distance, to provide fluid under pressure, so over­ small size and light weight may make it attractive In common with the Mark 7, the inlet porting of coming pipe losses and ensuring an adequate supply. where occasional running only is required. the Mark 8 is automatic. A groove is cut in each Aircraft Engineering http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Auxiliary Equipment

Aircraft Engineering and Aerospace Technology , Volume 26 (3): 1 – Mar 1, 1954

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032406
Publisher site
See Article on Publisher Site

Abstract

There is thus no need to pressurize the reservoir. unit is being produced by Vickers Incorporated, Auxiliary Equipment Oakman Boulevard, Detroit 32, Michigan. The unit consists of a two-stage pump driven b standard Vickers 3,000 lb./sq. in. hydraulic mot which is supplied from the main system. The Details of Some Components Used for stage of the booster pump is a centrifugal impel which is fed by gravity from the reservoir. The f Subsidiary Services in Aircraft is then passed on to the second stage, a vane pun from which it goes into the system supply line at to 100 lb./sq. in. The output of the unit ranges from 5 U.S. g New Lockheed Hydraulic Pump cylinder in such a position that it is partly uncovered min. at a differential pressure of 100 lb./sq. in. shortly before the plunger reaches the bottom of its 35 gal./min. at 18 lb./sq. in. differential. The weig A new enginc-driven hydraulic pump with a rated stroke. On the compression stroke the plunger covers is 9-1 lb. Depending on the motor size used delive maximum working pressure of 3,000 lb./sq. in., and a the inlet port and trapped fluid is forced through a is twenty-three to thirty-three times the fluid fl rated minimum delivery of 5-12 gal./min. has been passage leading from the top of the cylinder, past a through the driving hydraulic motor. announced by the Aircraft Division of the Lockheed delivery valve into an annular passage in the high- Hydraulic Brake Co. Ltd. pressure end cover leading to the outlet connexion. Gas Turbine-driven Generators This pump, which is known as the Mark 8, has The inlet passages on the new unit, however, have twice the output of the Mark 7, which, with a working The Solar Aircraft Company, San Diego 12, Ca been slightly re-designed, and the drive shaft has been pressure of 3,000 lb./sq. in. and a delivery rate of fornia, U.S.A., has introduced two airborne gcnerati modified and strengthened to meet the heavier de­ 2½ gal./min., was previously the largest-capacity sets powered by their Mars gas turbine, which d mand on it made by the higher output. pump made by Lockheed. livers over 40 h.p. One is an a.c./d.c. unit givi 'Non-flam' and other water-based fluids can be Work on the Mark 8 began when it became ap­ 8kva/14kw respectively, and the other a I4kw d used in hydraulic systems which are associated with parent that the demand for hydraulic power in some unit. They arc designed to operate at up to 20,000 the Mark 8 pump, and the shaft seals are resistant to of the larger aircraft of today and in types contem­ and over a temperature range of +130 deg. F. the synthetic turbine oils which are now becoming —65 deg. F. The starting system is automatic, an plated for the future would exceed the capacity of popular. the unit is protected with overspecd and ovcrheatin existing pumps. The following figures give a brief outline of the cut-outs. The arrangement of the circuit is shown Structurally, the new unit has many of the features performance of the Lockheed Mark 8 hydraulic FIG. 3. of the Mark 7, and might almost be described as a pump: 'double-banked Mark 7'. The Mark 7 is a seven- The turbine power unit consists of a ccntrifug Rated maximum working pressure, 3,000 lb./sq. in. cylinder radial plunger pump actuated by an eccentric compressor discharging to a single combustion cham Rated minimum delivery at 3,000 lb./sq. in. and ber. Burning gases are ducted to the radial inflo shaft which is integral with the driving shaft; the Mark 3,300 r.p.m., is 5-12 gal./min. single-stage turbine, which is mounted on the sam 8 has fourteen cylinders arranged in two radial banks, Approximate horse-power at the above speed and shaft as the compressor, and separated from it by and is actuated by a balanced two-throw eccentric pressure is 12-9. diaphragm. The shaft runs at 36,400 r.p.m. and this shaft. Because of the multiplicity of cylinders, the Rated maximum cruising speed, 3,300 r.p.m. reduced by a pair of spiral bevel gears to 4,500 an hydraulic system is free from the pressure pulses Overspecd at 3,000 lb./sq. in. 4,000 r.p.m. 6,000 r.p.m. The unit will run on high-octane gasoline which arc unavoidable when pumps with com­ paratively few cylinders arc employed. jet fuels or diescl oil, the fuel consumption being o the order of 3}-4 lb. per kw-hour. The weights a No attempt has been made to give the new pump Hydraulic Fluid Booster Pump 350 lb. for the a.c./d.c. set and 230 lb. for the d.c. set greater versatility than that of the Mark 7. It is, like The overhaul life is quoted as 500 hours, with a 60 the other, a straight-forward pumping unit with no An example of current American practice in hy­ hour routine service. off-loading devices or other features that might impair draulic equipment is illustrated in no. 2. It is a its efficiency or destroy its simplicity. It is also cool hydraulic booster pump which is mounted on the With its high fuel consumption the number o fluid reservoir, when the system pumps are at some applications for such a unit will be limited, but the running. distance, to provide fluid under pressure, so over­ small size and light weight may make it attractive In common with the Mark 7, the inlet porting of coming pipe losses and ensuring an adequate supply. where occasional running only is required. the Mark 8 is automatic. A groove is cut in each Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Mar 1, 1954

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