GB807071A - Improvements in or relating to gas compressing plant - Google Patents
Improvements in or relating to gas compressing plantInfo
- Publication number
- GB807071A GB807071A GB2455255A GB2455255A GB807071A GB 807071 A GB807071 A GB 807071A GB 2455255 A GB2455255 A GB 2455255A GB 2455255 A GB2455255 A GB 2455255A GB 807071 A GB807071 A GB 807071A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pressure
- compressor
- pressure compressor
- valve
- pass valve
- 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.)
- Expired
Links
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
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
807,071. Centrifugal compressors; gas turbine plant POWER JETS (RESEARCH & DEVELOPMENT) Ltd. Aug. 3, 1956 [Aug. 26, 1955], No. 24552/55. Addition to 774,391. Classes 110 (1) and 110 (3). [Also in Group XXIX] A compressor plant comprises separate low and high-pressure compressors connected in series and driven by separate turbines, the low-pressure compressor also supplying gas to the turbines by way of a heating system, and surging is prevented by a by-pass at the outlet of the high-pressure compressor, the by-pass valve being controlled by a pneumatic differential relay responsive to two gas pressures sensed by tappings at the high-pressure compressor. In the gas turbine plant described in the parent Specification, wherein the output from a lowpressure centrifugal air compressor is divided, part of it going through a two-stage highpressure centrifugal air compressor to the output and part directly to the combustion chamber and from there to the two separate turbines which separately drive the compressors; the surge-preventing by-pass valve 17, Fig. 4, is actuated pneumatically instead of hydraulically. The high-pressure compressor runs at a constant governor-controlled speed. Pressure tappings 28, 29 at the inlet and throat of a venturi flow meter situated at the intake or delivery of the high-pressure compressor communicate with corrugated diaphragms or, as shown, bellows 32, 33 of differing diameters, connected in opposition to a lever 40 pivoted about a fulcrum 41. A valve 37 carried by the lever 40 throttles the escape of air through a nozzle at the end of a pipe 38. Variations in the leak-off result in corresponding variations in the pressure in an air supply pipe 21 downstream of a restriction 39. This pressure is applied to a diaphragm 44 to operate the by-pass valve 17. A device 35 can alter the pressure to provide compensation for temperature variations sensed at 36. At normal rates of flow, the venturi is partly bypassed by a valve 31 which lifts at a load value just above the operating range of the surgepreventing control. The pipe 21 is connected to the outlet of the low-pressure compressor, and may incorporate a cooler. The venturi may be omitted, the flow measuring tappings then being taken from static points in an outlet duct wall or from a yawmeter. The yawmeter tapping points may comprise sensing holes 26, 27, Fig. 2, in small diameter tubes 25 in the leading edges of separate diffuser vanes 24 of the second-stage high-pressure compressor. The tubes 25 are adjustable to bring the holes 26, 27 to the required positions. A number of such pairs of holes may be disposed around the circumference of the compressor. A second and larger pneumatic relay may be interposed between the pneumatic relay and the by-pass valve 17. Mechanical or pneumatic feedback may be used.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2455255A GB807071A (en) | 1955-08-26 | 1955-08-26 | Improvements in or relating to gas compressing plant |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2455255A GB807071A (en) | 1955-08-26 | 1955-08-26 | Improvements in or relating to gas compressing plant |
Publications (1)
Publication Number | Publication Date |
---|---|
GB807071A true GB807071A (en) | 1959-01-07 |
Family
ID=10213415
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2455255A Expired GB807071A (en) | 1955-08-26 | 1955-08-26 | Improvements in or relating to gas compressing plant |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB807071A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3044683A (en) * | 1960-01-18 | 1962-07-17 | Schwitzer Corp | Pressure control for turbochargers |
FR2389785A1 (en) * | 1977-05-06 | 1978-12-01 | Alsthom Atlantique | Centrifugal compressor control system - has anti-pumping valve actuated by signal from flow direction sensing probe in outlet |
CN112664326A (en) * | 2020-12-11 | 2021-04-16 | 中国航空工业集团公司金城南京机电液压工程研究中心 | High-low pressure bleed air system |
-
1955
- 1955-08-26 GB GB2455255A patent/GB807071A/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3044683A (en) * | 1960-01-18 | 1962-07-17 | Schwitzer Corp | Pressure control for turbochargers |
FR2389785A1 (en) * | 1977-05-06 | 1978-12-01 | Alsthom Atlantique | Centrifugal compressor control system - has anti-pumping valve actuated by signal from flow direction sensing probe in outlet |
CN112664326A (en) * | 2020-12-11 | 2021-04-16 | 中国航空工业集团公司金城南京机电液压工程研究中心 | High-low pressure bleed air system |
CN112664326B (en) * | 2020-12-11 | 2022-09-06 | 中国航空工业集团公司金城南京机电液压工程研究中心 | High-low pressure bleed air system |
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