CN111287850A - Gas turbine lubricating system - Google Patents
Gas turbine lubricating system Download PDFInfo
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- CN111287850A CN111287850A CN202010193885.7A CN202010193885A CN111287850A CN 111287850 A CN111287850 A CN 111287850A CN 202010193885 A CN202010193885 A CN 202010193885A CN 111287850 A CN111287850 A CN 111287850A
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- oil
- pump
- oil pipe
- filter
- lubricating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- General Details Of Gearings (AREA)
Abstract
A gas turbine lubricating system relates to the technical field of gas turbines. The invention aims to solve the problems of high lubricating oil consumption, unstable system operation, easy equipment abrasion and poor safety of the conventional lubricating system. The invention comprises a first protective oil filter, a first centrifugal machine, a second protective oil filter, a main transmission case, a third protective oil filter, a front transmission case, a circulating oil tank, a lubricating oil cooler, an oil return filter, an oil supply filter, an air separator, a lower transmission case, a lubricating oil accessory, an oil-gas separation case and a fourth protective oil filter, wherein the lubricating oil accessory comprises a booster pump K pump, a return oil pump L pump, a return oil pump M pump, a return oil pump N pump, a return oil pump T pump and a return oil pump P pump. The invention is used for gas turbine lubrication.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a gas turbine lubricating system.
Background
The gas turbine lubricating system is used for providing proper lubricating oil for the gas turbine so as to meet the lubricating oil required by the gas turbine for lubricating and cooling during normal operation. When the gas turbine works normally, lubricating oil needs to be supplied to working surfaces of bearings, gears and the like to form a continuous oil film, and heat transmitted by friction and high-temperature parts is taken away, so that the parts are maintained in a normal working temperature range, and the service lives of the parts are prolonged. However, the conventional lubricating system has high consumption of lubricating oil, unstable system operation, easy equipment abrasion and poor safety.
Disclosure of Invention
The invention provides a gas turbine lubricating system in order to solve the problems that the conventional lubricating system is high in lubricating oil consumption, unstable in system operation, easy to cause equipment abrasion and poor in safety.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a gas turbine lubricating system comprises a first protective oil filter, a first centrifugal machine, a second protective oil filter, a main transmission box, a third protective oil filter, a front transmission box, a circulating oil box, a lubricating oil cooler, a first filter, a second filter, an air separator, a lower transmission box, a lubricating oil accessory, an oil-gas separation box and a fourth protective oil filter, wherein the lubricating oil accessory comprises a booster pump K pump, a scavenging pump L pump, a scavenging pump M pump, a scavenging pump N pump, a scavenging pump T pump and a scavenging pump P pump;
the output end of the circulating oil tank is connected with the inlet end of a first oil pipe, the outlet end of the first oil pipe is connected with the input end of a booster pump K pump, the output end of the booster pump K pump is connected with the inlet end of a second oil pipe, the outlet end of the second oil pipe is connected with the input end of a second filter, the output end of the second filter is respectively connected with the inlet ends of a third oil pipe, a fourth oil pipe, a fifth oil pipe and a sixth oil pipe, the outlet end of the third oil pipe is connected with the input end of a first protective oil filter, the outlet end of the fourth oil pipe is connected with the input end of a second protective oil filter, the outlet end of the fifth oil pipe is connected with the input end of the third protective oil filter, the outlet end of the sixth oil pipe is connected with the input end of the fourth protective oil filter, the output end of the first protective oil filter is connected with the lubricating oil input end of the gas turbine bearing component, the output end of the third protective oil filter is connected with the lubricating oil input ends of the main transmission case, the rear casing of the high-pressure compressor, the low-pressure turbine supporting ring and the power turbine supporting ring, the output end of the fourth protective oil filter is connected with the lubricating oil input ends of the front casing of the low-pressure compressor and the transition section, and the lubricating oil output end of the main transmission case is connected with the lubricating oil input end of the lower transmission case;
the lubricating oil output end of the front casing of the low-pressure compressor is connected with the inlet end of a seventh oil pipe, the outlet end of the seventh oil pipe is connected with the first lubricating oil input end of the oil-gas separation box, the lubricating oil output end of the transition section is connected with the inlet end of a sixteenth oil pipe, the outlet end of the sixteenth oil pipe is connected with the second lubricating oil input end of the oil-gas separation box, the lubricating oil output end of the oil-gas separation box is connected with the inlet end of an eighth oil pipe, and the outlet end of the eighth oil pipe is connected with the input end of an oil return pump N;
the lubricating oil output ends of the rear casing of the high-pressure compressor and the low-pressure turbine supporting ring are respectively connected with the lubricating oil input end of the lower transmission case, the lubricating oil output end of the lower transmission case is connected with the inlet end of a ninth oil pipe, and the outlet end of the ninth oil pipe is connected with the input end of a P pump of the oil return pump;
the lubricating oil output end of the power turbine supporting ring is connected with the inlet end of a tenth oil pipe, and the outlet end of the tenth oil pipe is connected with the input end of an L pump of the oil return pump;
the oil-gas mixture output ends of the low-pressure compressor front casing, the transition section, the high-pressure compressor rear casing, the low-pressure turbine supporting ring and the power turbine supporting ring are connected with the oil-gas mixture input end of the main transmission case, the oil-gas mixture output end of the main transmission case is connected with the oil-gas mixture input ends of the first centrifugal machine and the second centrifugal machine respectively, the lubricating oil output end of the first centrifugal machine is connected with the inlet end of an eleventh oil pipe, the outlet end of the eleventh oil pipe is connected with the input end of a scavenge pump T pump, the lubricating oil output end of the second centrifugal machine is connected with the inlet end of a twelfth oil pipe, the outlet end of the twelfth oil pipe is connected with the input end of a scavenge pump M pump, and the gas output ends of the;
the output ends of the oil return pump N, the oil return pump P, the oil return pump L, the oil return pump T and the oil return pump M are respectively connected with the input end of an air separator, the lubricating oil output end of the air separator is connected with the inlet end of a thirteenth oil pipe, the outlet end of the thirteenth oil pipe is connected with the input end of a first filter, the output end of the first filter is connected with the inlet end of a fourteenth oil pipe, the outlet end of the fourteenth oil pipe is connected with the input end of a lubricating oil cooler, the output end of the lubricating oil cooler is connected with the inlet end of a fifteenth oil pipe, and the outlet end of the fifteenth oil pipe is connected with the lubricating oil input end of a circulating oil tank.
Compared with the prior art, the invention has the following beneficial effects:
the invention relates to a gas turbine lubricating system used in the ship industry, belongs to the energy power industry, and particularly relates to a forced oil return circulating lubricating system which is used for lubricating and cooling a bearing part and a gear meshing part of a gas turbine under all working conditions of the gas turbine and comprises an oil supply system, an oil return system and a ventilation system. The invention provides a gas turbine lubricating system which is stable in performance, reliable in work, convenient to maintain, reasonable in measuring point arrangement, low in lubricating oil consumption and high in safety. Lubricating oil is supplied to the gas turbine in the full working condition range, so that the friction and the abrasion of the moving dual surfaces of the gas turbine are reduced, the corrosion and the surface hardening of the gas turbine are prevented, the heat generated by the friction and the heat transmitted to the lubricating oil by high-temperature parts are transmitted, hard inclusions formed between the dual surfaces are taken away, and the reliable work of the gas turbine is ensured.
Drawings
Fig. 1 is a schematic diagram of the present invention.
Detailed Description
The first embodiment is as follows: the embodiment is described with reference to fig. 1, and the gas turbine lubricating system according to the embodiment includes a first protective oil filter 1, a first centrifuge 2, a second centrifuge 3, a second protective oil filter 4, a main transmission case 5, a third protective oil filter 6, a front transmission case 7, a circulating oil tank 8, a lubricating oil cooler 10, an oil return filter 11, an oil supply filter 15, an air separator 16, a lower transmission case 17, a lubricating oil accessory 19, an oil-gas separation case 22, and a fourth protective oil filter 24, where the lubricating oil accessory 19 includes a booster pump K, a scavenge pump L, a scavenge pump M, a scavenge pump N, a scavenge pump T, and a scavenge pump P;
the output end of the circulating oil tank 8 is connected with the inlet end of a first oil pipe 101, the outlet end of the first oil pipe 101 is connected with the input end of a booster pump K, the output end of the booster pump K is connected with the inlet end of a second oil pipe 102, the outlet end of the second oil pipe 102 is connected with the input end of an oil supply filter 15, the output end of the oil supply filter 15 is respectively connected with the inlet ends of a third oil pipe 103, a fourth oil pipe 104, a fifth oil pipe 105 and a sixth oil pipe 106, the outlet end of the third oil pipe 103 is connected with the input end of a first protective oil filter 1, the outlet end of the fourth oil pipe 104 is connected with the input end of a second protective oil filter 4, the outlet end of the fifth oil pipe 105 is connected with the input end of a third protective oil filter 6, the outlet end of the sixth oil pipe 106 is connected with the input end of a fourth protective oil filter 24, the output end of the first protective oil filter 1 is connected with the lubricating oil input end of a gas turbine bearing component, the, the output end of the third protective oil filter 6 is connected with the lubricating oil input ends of the main transmission case 5, the rear casing of the high-pressure compressor, the low-pressure turbine supporting ring and the power turbine supporting ring, the output end of the fourth protective oil filter 24 is connected with the lubricating oil input ends of the front casing and the transition section of the low-pressure compressor, and the lubricating oil output end of the main transmission case 5 is connected with the lubricating oil input end of the lower transmission case 17;
the lubricating oil output end of the front casing of the low-pressure compressor is connected with the inlet end of a seventh oil pipe 107, the outlet end of the seventh oil pipe 107 is connected with the first lubricating oil input end of an oil-gas separation box 22, the lubricating oil output end of the transition section is connected with the inlet end of a sixteenth oil pipe 116, the outlet end of the sixteenth oil pipe 116 is connected with the second lubricating oil input end of the oil-gas separation box 22, the lubricating oil output end of the oil-gas separation box 22 is connected with the inlet end of an eighth oil pipe 108, and the outlet end of the eighth oil pipe 108 is connected with the input end of an oil return pump N;
the lubricating oil output ends of the high-pressure compressor rear casing and the low-pressure turbine supporting ring are respectively connected with the lubricating oil input end of the lower transmission case 17, the lubricating oil output end of the lower transmission case 17 is connected with the inlet end of a ninth oil pipe 109, and the outlet end of the ninth oil pipe 109 is connected with the input end of a scavenging pump P;
the lubricating oil output end of the power turbine supporting ring is connected with the inlet end of a tenth oil pipe 110, and the outlet end of the tenth oil pipe 110 is connected with the input end of an oil return pump L pump;
the oil-gas mixture output ends of the low-pressure compressor front casing, the transition section, the high-pressure compressor rear casing, the low-pressure turbine support ring and the power turbine support ring are connected with the oil-gas mixture input end of the main transmission case 5, the oil-gas mixture output end of the main transmission case 5 is connected with the oil-gas mixture input ends of the first centrifugal machine 2 and the second centrifugal machine 3 respectively, the lubricating oil output end of the first centrifugal machine 2 is connected with the inlet end of an eleventh oil pipe 111, the outlet end of the eleventh oil pipe 111 is connected with the input end of a scavenge pump T pump, the lubricating oil output end of the second centrifugal machine 3 is connected with the inlet end of a twelfth oil pipe 112, the outlet end of the twelfth oil pipe 112 is connected with the input end of a scavenge pump M pump, and the gas output ends of the first centrifugal;
the output ends of the scavenge pump N, the scavenge pump P, the scavenge pump L, the scavenge pump T and the scavenge pump M are respectively connected with the input end of the air separator 16, the lubricating oil output end of the air separator 16 is connected with the inlet end of a thirteenth oil pipe 113, the outlet end of the thirteenth oil pipe 113 is connected with the input end of an oil return filter 11, the output end of the oil return filter 11 is connected with the inlet end of a fourteenth oil pipe 114, the outlet end of the fourteenth oil pipe 114 is connected with the input end of a lubricating oil cooler 10, the output end of the lubricating oil cooler 10 is connected with the inlet end of a fifteenth oil pipe 115, and the outlet end of the fifteenth oil pipe 115 is connected with the lubricating oil input end of the circulating oil tank 8.
In this embodiment, when the gas turbine is in operation, the booster pump K in the lubricating oil accessory 19 pumps lubricating oil from the circulating oil tank 8, and the lubricating oil is filtered by the oil supply filter 15, then is supplied to the gas turbine bearing component, the main transmission case 5, the high-pressure compressor rear case, the low-pressure turbine support ring, the power turbine support ring, the low-pressure compressor front case, the transition section, and the lower transmission case 17 through the first protective oil filter 1, the second protective oil filter 4, the third protective oil filter 6, and the fourth protective oil filter 24, respectively, and is pumped back by the scavenge pump in the lubricating oil accessory 19 to lubricate and cool these components.
The working lubricating oil from the low-pressure compressor front casing and the transition section is pumped back by a scavenging pump N in the lubricating oil accessory 19 through the oil-gas separation box 22, the working lubricating oil from the high-pressure compressor rear casing and the low-pressure turbine supporting ring enters the lower transmission box 17 and is pumped back by a scavenging pump P in the lubricating oil accessory 19, and the working lubricating oil from the power turbine supporting ring is pumped back by a scavenging pump L in the lubricating oil accessory 19.
The oil-gas mixture from the low-pressure compressor front casing, the transition section, the high-pressure compressor rear casing, the low-pressure turbine supporting ring and the power turbine supporting ring enters the main transmission case 5, the first centrifugal machine 2 and the second centrifugal machine 3 finally separate the lubricating oil from the oil-gas mixture, and the separated air is discharged to the atmosphere. The oil separated by the first centrifuge 2 and the second centrifuge 3 is pumped back by the scavenge pump T and scavenge pump M in the oil attachment 19, respectively.
The lubricating oil drawn back by the lubricating oil attachment 19 is returned to the circulating oil tank 8 via the air separator 16, the return oil filter 11 and the lubricating oil cooler 10.
The second embodiment is as follows: the present embodiment will be described with reference to fig. 1, and the oil filter 15 according to the present embodiment is provided with a pressure sensor 13. Other components and connection modes are the same as those of the first embodiment.
The lubrication system oil supply pressure is detected using a pressure sensor 13.
The third concrete implementation mode: the present embodiment will be described with reference to fig. 1, and the oil feed filter 15 of the present embodiment is further provided with a pressure annunciator 14. Other components and connection modes are the same as those of the second embodiment.
A pressure annunciator 14 is employed to provide protection against gas turbine inlet oil pressure drop.
The fourth concrete implementation mode: in the present embodiment, the first oil pipe 101 is provided with the first thermal resistance converter 9, the thirteenth oil pipe 113 is provided with the second thermal resistance converter 12, and the eighth oil pipe 108 is provided with the third thermal resistance converter 21, as described with reference to fig. 1. The other components and the connection mode are the same as those of the first embodiment, the second embodiment or the third embodiment.
A thermal resistance converter is adopted to detect the temperature of lubricating oil at the inlet of the gas turbine, the temperature of the lubricating oil at the outlet of an oil-gas separation box of the gas turbine and the temperature of the lubricating oil of a front oil return pipeline of a lubricating oil cooler.
The fifth concrete implementation mode: referring to fig. 1, the first magnetic metal dust signal 18 is provided at the input end of the air separator 16, the second magnetic metal dust signal 23 is provided on the seventh oil pipe 107, and the third magnetic metal dust signal 20 is provided on the sixteenth oil pipe 116. The other components and the connection mode are the same as those of the fourth embodiment.
The magnetic metal chip annunciator is used for diagnosing the abrasion states of bearing parts and gears of the gas turbine.
Although the invention herein has been described with reference to particular embodiments, it is to be understood that these embodiments are merely illustrative of the principles and applications of the present invention. It is therefore to be understood that numerous modifications may be made to the illustrative embodiments and that other arrangements may be devised without departing from the spirit and scope of the present invention as defined by the appended claims. It should be understood that features described in different dependent claims and herein may be combined in ways different from those described in the original claims. It is also to be understood that features described in connection with individual embodiments may be used in other described embodiments.
Claims (5)
1. A gas turbine lubrication system, characterized by: the gas turbine lubricating system comprises a first protective oil filter (1), a first centrifugal machine (2), a second centrifugal machine (3), a second protective oil filter (4), a main transmission case (5), a third protective oil filter (6), a front transmission case (7), a circulating oil tank (8), a lubricating oil cooler (10), an oil return filter (11), an oil supply filter (15), an air separator (16), a lower transmission case (17), a lubricating oil accessory (19), an oil-gas separation case (22) and a fourth protective oil filter (24), wherein the lubricating oil accessory (19) comprises a booster pump K pump, a scavenging pump L pump, a scavenging pump M pump, a scavenging pump N pump, a scavenging pump T pump and a scavenging pump P pump;
the output end of a circulating oil tank (8) is connected with the inlet end of a first oil pipe (101), the outlet end of the first oil pipe (101) is connected with the input end of a booster pump K, the output end of the booster pump K is connected with the inlet end of a second oil pipe (102), the outlet end of the second oil pipe (102) is connected with the input end of an oil supply filter (15), the output end of the oil supply filter (15) is respectively connected with the inlet ends of a third oil pipe (103), a fourth oil pipe (104), a fifth oil pipe (105) and a sixth oil pipe (106), the outlet end of the third oil pipe (103) is connected with the input end of a first protective oil filter (1), the outlet end of the fourth oil pipe (104) is connected with the input end of a second protective oil filter (4), the outlet end of the fifth oil pipe (105) is connected with the input end of a third protective oil filter (6), and the outlet end of the sixth oil pipe (106) is connected with the input end of a, the output end of a first protective oil filter (1) is connected with the lubricating oil input end of a gas turbine bearing component, the output end of a second protective oil filter (4) is connected with the lubricating oil input end of a main transmission case (5), the output end of a third protective oil filter (6) is connected with the lubricating oil input ends of the main transmission case (5), a high-pressure compressor rear case, a low-pressure turbine support ring and a power turbine support ring, the output end of a fourth protective oil filter (24) is connected with the lubricating oil input ends of a low-pressure compressor front case and a transition section, and the lubricating oil output end of the main transmission case (5) is connected with the lubricating oil input end of a lower transmission case (17);
the lubricating oil output end of a front casing of the low-pressure compressor is connected with the inlet end of a seventh oil pipe (107), the outlet end of the seventh oil pipe (107) is connected with the first lubricating oil input end of an oil-gas separation box (22), the lubricating oil output end of a transition section is connected with the inlet end of a sixteenth oil pipe (116), the outlet end of the sixteenth oil pipe (116) is connected with the second lubricating oil input end of the oil-gas separation box (22), the lubricating oil output end of the oil-gas separation box (22) is connected with the inlet end of an eighth oil pipe (108), and the outlet end of the eighth oil pipe (108) is connected with the input end of an oil-returning pump N;
the lubricating oil output ends of a rear casing of the high-pressure compressor and a low-pressure turbine supporting ring are respectively connected with the lubricating oil input end of a lower transmission case (17), the lubricating oil output end of the lower transmission case (17) is connected with the inlet end of a ninth oil pipe (109), and the outlet end of the ninth oil pipe (109) is connected with the input end of a scavenging pump P;
the lubricating oil output end of the power turbine supporting ring is connected with the inlet end of a tenth oil pipe (110), and the outlet end of the tenth oil pipe (110) is connected with the input end of an oil return pump L pump;
the oil-gas mixture output ends of the low-pressure compressor front casing, the transition section, the high-pressure compressor rear casing, the low-pressure turbine supporting ring and the power turbine supporting ring are connected with the oil-gas mixture input end of the main transmission case (5), the oil-gas mixture output end of the main transmission case (5) is connected with the oil-gas mixture input ends of the first centrifugal machine (2) and the second centrifugal machine (3), the lubricating oil output end of the first centrifugal machine (2) is connected with the inlet end of an eleventh oil pipe (111), the outlet end of the eleventh oil pipe (111) is connected with the input end of a scavenge pump T pump, the lubricating oil output end of the second centrifugal machine (3) is connected with the inlet end of a twelfth oil pipe (112), the outlet end of the twelfth oil pipe (112) is connected with the input end of a scavenge pump M, and the gas output ends of the first centrifugal machine (2) and the second centrifugal machine (3) are connected with a gas discharge pipe respectively;
the output ends of an oil return pump N, an oil return pump P, an oil return pump L, an oil return pump T and an oil return pump M are respectively connected with the input end of an air separator (16), the lubricating oil output end of the air separator (16) is connected with the inlet end of a thirteenth oil pipe (113), the outlet end of the thirteenth oil pipe (113) is connected with the input end of an oil return filter (11), the output end of the oil return filter (11) is connected with the inlet end of a fourteenth oil pipe (114), the outlet end of the fourteenth oil pipe (114) is connected with the input end of a lubricating oil cooler (10), the output end of the lubricating oil cooler (10) is connected with the inlet end of a fifteenth oil pipe (115), and the outlet end of the fifteenth oil pipe (115) is connected with the lubricating oil input end of a circulating oil tank (8).
2. The gas turbine lubrication system of claim 1, wherein: and a pressure sensor (13) is arranged on the oil supply filter (15).
3. The gas turbine lubrication system of claim 2, wherein: and a pressure annunciator (14) is also arranged on the oil supply filter (15).
4. A gas turbine lubrication system according to claim 1, 2 or 3, characterised in that: the oil pipe is characterized in that a first thermal resistance converter (9) is arranged on the first oil pipe (101), a second thermal resistance converter (12) is arranged on the thirteenth oil pipe (113), and a third thermal resistance converter (21) is arranged on the eighth oil pipe (108).
5. The gas turbine lubrication system of claim 4, wherein: the input end of the air separator (16) is provided with a first magnetic metal chip annunciator (18), the seventh oil pipe (107) is provided with a second magnetic metal chip annunciator (23), and the sixteenth oil pipe (116) is provided with a third magnetic metal chip annunciator (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010193885.7A CN111287850A (en) | 2020-03-12 | 2020-03-12 | Gas turbine lubricating system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010193885.7A CN111287850A (en) | 2020-03-12 | 2020-03-12 | Gas turbine lubricating system |
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| Publication Number | Publication Date |
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| CN111287850A true CN111287850A (en) | 2020-06-16 |
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| CN202010193885.7A Pending CN111287850A (en) | 2020-03-12 | 2020-03-12 | Gas turbine lubricating system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112780415A (en) * | 2021-02-22 | 2021-05-11 | 中国航发沈阳发动机研究所 | Double-margin lubricating oil difference detection method and device for aircraft engine lubricating oil system |
| CN113624487A (en) * | 2021-08-13 | 2021-11-09 | 中国船舶重工集团公司第七O三研究所无锡分部 | Bushing suitable for gas turbine transmission box body test and mounting method thereof |
| CN114233480A (en) * | 2021-12-13 | 2022-03-25 | 中国船舶重工集团公司第七0三研究所 | Gas turbine transmission system |
| CN114542294A (en) * | 2022-02-16 | 2022-05-27 | 中国航发沈阳发动机研究所 | High mach number turbine engine central transmission system overall structure |
-
2020
- 2020-03-12 CN CN202010193885.7A patent/CN111287850A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112780415A (en) * | 2021-02-22 | 2021-05-11 | 中国航发沈阳发动机研究所 | Double-margin lubricating oil difference detection method and device for aircraft engine lubricating oil system |
| CN112780415B (en) * | 2021-02-22 | 2022-03-04 | 中国航发沈阳发动机研究所 | Dual-redundancy lubricating oil difference detection method and device for aircraft engine lubricating oil system |
| CN113624487A (en) * | 2021-08-13 | 2021-11-09 | 中国船舶重工集团公司第七O三研究所无锡分部 | Bushing suitable for gas turbine transmission box body test and mounting method thereof |
| CN113624487B (en) * | 2021-08-13 | 2023-08-15 | 中国船舶重工集团公司第七O三研究所无锡分部 | Bushing suitable for gas turbine transmission case test and mounting method thereof |
| CN114233480A (en) * | 2021-12-13 | 2022-03-25 | 中国船舶重工集团公司第七0三研究所 | Gas turbine transmission system |
| CN114542294A (en) * | 2022-02-16 | 2022-05-27 | 中国航发沈阳发动机研究所 | High mach number turbine engine central transmission system overall structure |
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