A lubrication system for a gas turbine unit

Abstract

A lubrication system for a gas turbine unit, which relates to a lubrication system, specifically to a lubrication system for a gas turbine unit. The present invention aims to solve the problems of unstable performance, poor working reliability, inconvenient maintenance, unreasonable measurement point arrangement, high lubricating oil consumption, and low safety of the existing lubrication system for gas turbine units. The present invention includes a static oil-gas separator, a small oil-gas separator, an oil-gas separation tank, a circulating oil tank, a lubricating oil assembly, a return oil double oil filter, a plate heat exchanger, an intermediate small oil tank, and an inlet oil double oil filter. The present invention belongs to the field of energy and power.

Description

Technical Field

[0001] The present invention relates to a lubrication system, and particularly to a lubrication system for a gas turbine unit, belonging to the field of energy and power. Background Art

[0002] The gas turbine lubrication system is used to provide suitable lubricating oil for the gas turbine to meet the lubricating and cooling requirements of the gas turbine during normal operation. When the gas turbine is operating normally, lubricating oil needs to be supplied to the working surfaces such as bearings and gears to form a continuous oil film, which takes away the heat transmitted from friction and high-temperature parts to maintain the components within the normal working temperature range and improve the service life of the components. Summary of the Invention

[0003] In order to solve the problems of unstable performance, poor working reliability, inconvenient maintenance, unreasonable measuring point arrangement, high lubricating oil consumption, and low safety of the existing lubrication system for gas turbine units, the present invention further provides a lubrication system for gas turbine units.

[0004] The technical solution adopted by the present invention to solve the above problems is as follows: The present invention includes a static oil-gas separator, a small oil-gas separator, an oil-gas separation tank, a circulating oil tank, a lubricating oil assembly, a return oil double oil filter, a plate heat exchanger, an intermediate small oil tank, and an inlet oil double oil filter;

[0005] The static oil-gas separator is connected to the small oil-gas separator, the small oil-gas separator is connected to the oil-gas separation tank, the oil-gas separation tank is connected to the lubricating oil assembly, the oil-gas separation tank is connected to the gas turbine, the small oil-gas separator is connected to the lubricating oil assembly, the lubricating oil assembly is connected to the gas turbine through the intermediate small oil tank, the lubricating oil assembly is connected to the return oil double oil filter through the plate heat exchanger, the return oil double oil filter is connected to the circulating oil tank, the inlet oil double oil filter is connected to the gas turbine, the inlet oil double oil filter is connected to the circulating oil tank, and the inlet oil double oil filter is connected to the lubricating oil assembly.

[0006] Further, the present invention includes a first pressure signaler, a second pressure signaler, and a third pressure signaler; the first pressure signaler, the second pressure signaler, and the third pressure signaler are installed on the oil path between the inlet oil double oil filter and the gas turbine.

[0007] Further, the present invention further includes a first throttle washer, a second throttle washer, and a bypass valve; the first throttle washer is installed on the oil path between the static oil-gas separator and the small oil-gas separator, the bypass valve is installed on the oil path between the inlet oil double oil filter and the circulating oil tank, the second throttle washer is installed on the oil path between the inlet oil double oil filter and the circulating oil tank, and the second throttle washer is located between the bypass valve and the circulating oil tank.

[0008] Further, the present invention further includes a first protection oil filter, a second protection oil filter, a third protection oil filter, a fourth protection oil filter, a fifth protection oil filter, a sixth protection oil filter, a seventh protection oil filter, an eighth protection oil filter, and a ninth protection oil filter;

[0009] The first protection oil filter, the second protection oil filter, the third protection oil filter, the fourth protection oil filter, and the fifth protection oil filter are installed on the gas turbine. The first protection oil filter, the second protection oil filter, the third protection oil filter, the fourth protection oil filter, and the fifth protection oil filter are all connected to the inlet oil duplex filter and are all connected to the circulating oil tank; The sixth protection oil filter and the ninth protection oil filter are installed on the circulating oil tank. The seventh protection oil filter and the eighth protection oil filter are installed on the lower drive box connected to the lubricating oil assembly. The ninth protection oil filter is connected to the lubricating oil assembly.

[0010] Further, the present invention further includes a first magnetic metal chip signaler, a second magnetic metal chip signaler, a third magnetic metal chip signaler, a fourth magnetic metal chip signaler, and a fifth magnetic metal chip signaler;

[0011] The first magnetic metal chip signaler, the second magnetic metal chip signaler, and the third magnetic metal chip signaler are installed on the oil path connecting the oil-gas separation tank and the gas turbine. The seventh magnetic metal chip signaler is installed on the oil path connecting the lubricating oil assembly and the oil-gas separation tank. The fifth magnetic metal chip signaler is installed on the oil path connecting the intermediate small oil tank and the gas turbine.

[0012] Further, the present invention further includes a first temperature sensor, a second temperature sensor, a third temperature sensor, a fourth temperature sensor, a fifth temperature sensor, and a sixth temperature sensor;

[0013] The first temperature sensor, the second temperature sensor, and the third temperature sensor are installed on the oil path connecting the oil-gas separation tank and the gas turbine. The fourth temperature sensor is installed on the circulating oil tank. The fifth temperature sensor is installed on the oil path connecting the lubricating oil assembly and the plate heat exchanger. The sixth temperature sensor is installed on the oil path connecting the intermediate small oil tank and the gas turbine.

[0014] Further, the present invention further includes a first liquid level signaler and a second liquid level signaler; The first liquid level signaler and the second liquid level signaler are installed on the circulating oil tank.

[0015] Further, the present invention further includes a first stop valve and a second stop valve. The first stop valve and the second stop valve are installed on the circulating oil tank.

[0016] Further, the present invention further includes a first differential pressure signaler and a second differential pressure signaler. The first differential pressure signaler is installed on the return oil duplex filter, and the second differential pressure signaler is installed on the inlet oil duplex filter.

[0017] Furthermore, the present invention further includes a first pressure sensor and a second pressure sensor. The first pressure sensor is installed on the oil path between the lubricating oil assembly and the plate heat exchanger, and the second pressure sensor is installed on the oil path between the double oil inlet circuit and the gas turbine.

[0018] The beneficial effects of the present invention are as follows: lubricating oil is supplied to the gas turbine within the full operating range, reducing the friction and wear of the moving mating surfaces of the gas turbine, preventing their corrosion and surface hardening, transferring away the heat generated by friction and the heat transferred from high-temperature parts to the lubricating oil, removing the hard inclusions formed between the mating surfaces, and ensuring the reliable operation of the gas turbine.

[0019] A pressure sensor is used to detect the oil supply and return pressures of the lubrication system.

[0020] A pressure signaler is used to set the protection for the decrease in the lubricating oil pressure at the inlet of the gas turbine. When starting the gas turbine, according to the signal of the pressure signaler, the start of the gas turbine is stopped. When the lubricating oil pressure at the inlet of the gas turbine drops to the allowable value, according to the signal of another pressure signaler, the gas turbine is reduced to the idling condition. When the inlet lubricating oil pressure continues to drop, the third pressure signaler issues a signal for fault shutdown.

[0021] A temperature sensor is used to detect the lubricating oil temperature at the inlet of the gas turbine, the lubricating oil temperature at the outlet of the gas turbine lubricating oil cavity, and the lubricating oil temperature in the return oil pipeline in front of the plate heat exchanger.

[0022] A differential pressure signaler is used to monitor the fouling of the double oil inlet filter and the double oil return filter. When the differential pressure reaches the set value of the differential pressure signaler, an alarm for oil filter fouling is issued.

[0023] A magnetic metal chip signaler is used to diagnose the wear state of the bearing components and gears of the gas turbine.

[0024] A liquid level signaler is used to ensure an alarm when the liquid level in the gas turbine circulating oil tank is lower than the specified value.

[0025] Redundant settings of the double oil inlet filter and the double oil return filter are adopted, and a protection oil filter is set at the inlet of each casing to ensure the safe operation of the gas turbine.

[0026] A bypass valve and a throttle washer are used to limit the lubricating oil supply amount during the start-up and shutdown of the gas turbine.

[0027] The present invention is a lubrication system for a gas turbine unit, with stable performance, reliable operation, convenient maintenance, reasonable measuring point arrangement, low lubricating oil consumption, and high safety. Brief Description of the Drawings

[0028] Figure 1 It is a schematic diagram of the overall structure of the present invention. Detailed Embodiment

[0029] Specific Embodiment 1: Combined with Figure 1 Describe this embodiment. The lubrication system of a gas turbine unit described in this embodiment includes a static oil-gas separator 1, a small oil-gas separator 5, an oil-gas separation tank 18, a circulating oil tank 20, a lubricating oil assembly 29, a return double oil filter 31, a plate heat exchanger 33, an intermediate small oil tank 36, and an inlet double oil filter 39;

[0030] The static oil-gas separator 1 is connected to the small oil-gas separator 5, the small oil-gas separator 5 is connected to the oil-gas separation tank 18, the oil-gas separation tank 18 is connected to the lubricating oil assembly 29, the oil-gas separation tank 18 is connected to the gas turbine, the small oil-gas separator 5 is connected to the lubricating oil assembly 29, the lubricating oil assembly 29 is connected to the gas turbine through the intermediate small oil tank 36, the lubricating oil assembly 29 is connected to the return double oil filter 31 through the plate heat exchanger 33, the return double oil filter 31 is connected to the circulating oil tank 20, the inlet double oil filter 39 is connected to the gas turbine, the inlet double oil filter 39 is connected to the circulating oil tank 20, and the inlet double oil filter 39 is connected to the lubricating oil assembly 29.

[0031] Specific Embodiment 2: Combined with Figure 1 Describe this embodiment. The lubrication system of a gas turbine unit described in this embodiment further includes a first pressure signaler 2, a second pressure signaler 3, and a third pressure signaler 4; the first pressure signaler 2, the second pressure signaler 3, and the third pressure signaler 4 are installed on the oil path between the inlet double oil filter 39 and the gas turbine.

[0032] The first pressure signaler 2, the second pressure signaler 3, and the third pressure signaler 4 are used to set the protection for the decrease in the lubricating oil pressure at the gas turbine inlet. When starting the gas turbine, according to the signal of the first pressure signaler 2, the start of the gas turbine is stopped. When the lubricating oil pressure at the gas turbine inlet drops to the allowable value, according to the signal of the first pressure signaler 2, the gas turbine is reduced to the idle speed condition. When the inlet lubricating oil pressure continues to drop, according to the signal sent by the second pressure signaler 3, the gas turbine is shut down due to a fault.

[0033] Other compositions and connection relationships are the same as those in Specific Embodiment 1.

[0034] Specific Embodiment 3: Combined with Figure 1 Describe this embodiment. The lubrication system of a gas turbine unit described in this embodiment further includes a first throttle washer 6, a second throttle washer 42, and a bypass valve 43; the first throttle washer 6 is installed on the oil path between the static oil-gas separator 1 and the small oil-gas separator 5, the bypass valve 43 is installed on the oil path between the inlet double oil filter 39 and the circulating oil tank 20, the second throttle washer 42 is installed on the oil path between the inlet double oil filter 39 and the circulating oil tank 20, and the second throttle washer 42 is located between the bypass valve 43 and the circulating oil tank 20.

[0035] The lubricating oil supply amount during the start-up and shutdown of the gas turbine is restricted by using a bypass valve 43 and a second throttle washer 42.

[0036] Other components and connection relationships are the same as those in the first specific embodiment.

[0037] Specific embodiment four: Figure 1 This embodiment is described in combination with

[0038] A gas turbine unit lubrication system according to this embodiment further includes a first protection oil filter 7, a second protection oil filter 8, a third protection oil filter 9, a fourth protection oil filter 10, a fifth protection oil filter 11, a sixth protection oil filter 19, a seventh protection oil filter 26, an eighth protection oil filter 27, and a ninth protection oil filter 30;

[0039] The first protection oil filter 7, the second protection oil filter 8, the third protection oil filter 9, the fourth protection oil filter 10, the fifth protection oil filter 11 are installed on the gas turbine. The first protection oil filter 7, the second protection oil filter 8, the third protection oil filter 9, the fourth protection oil filter 10, the fifth protection oil filter 11 are all connected to the inlet double oil filter 39, and the first protection oil filter 7, the second protection oil filter 8, the third protection oil filter 9, the fourth protection oil filter 10, the fifth protection oil filter 11 are all connected to the circulating oil tank 20; The sixth protection oil filter 19 and the ninth protection oil filter 30 are installed on the circulating oil tank 20, the seventh protection oil filter 26 and the eighth protection oil filter 27 are installed on the lower transmission case connected to the lubricating oil assembly 29, and the ninth protection oil filter 30 is connected to the lubricating oil assembly 29.

[0040] Other components and connection relationships are the same as those in the first specific embodiment.

[0041] Specific embodiment five: Figure 1 This embodiment is described in combination with

[0042] The first magnetic metal chip signaler 12, the second magnetic metal chip signaler 14, and the third magnetic metal chip signaler 16 are installed on the oil path connecting the oil-gas separation tank 18 and the gas turbine. The seventh magnetic metal chip signaler 28 is installed on the oil path connecting the lubricating oil assembly 29 and the oil-gas separation tank 18. The fifth magnetic metal chip signaler 38 is installed on the oil path connecting the intermediate small oil tank 36 and the gas turbine.

[0043] The wear states of the bearing components and gears of the gas turbine are diagnosed by using the first magnetic metal chip signaler 12, the second magnetic metal chip signaler 14, the third magnetic metal chip signaler 16, the fourth magnetic metal chip signaler 28, and the fifth magnetic metal chip signaler 38.

[0044] Other compositions and connection relationships are the same as those in the first specific embodiment.

[0045] Specific embodiment six: Figure 1 To describe this embodiment, the lubrication system of a gas turbine unit in this embodiment further includes a first temperature sensor 13, a second temperature sensor 15, a third temperature sensor 17, a fourth temperature sensor 25, a fifth temperature sensor 35, and a sixth temperature sensor 37;

[0046] The first temperature sensor 13, the second temperature sensor 15, and the third temperature sensor 17 are installed on the oil pipeline connecting the oil-gas separation tank 18 and the gas turbine. The fourth temperature sensor 25 is installed on the circulation oil tank 20. The fifth temperature sensor 35 is installed on the oil pipeline connecting the lubricating oil assembly 29 and the plate heat exchanger 33. The sixth temperature sensor 37 is installed on the oil pipeline connecting the intermediate small oil tank 36 and the gas turbine.

[0047] The first temperature sensor 13, the second temperature sensor 15, the third temperature sensor 17, the fourth temperature sensor 25, the fifth temperature sensor 35, and the sixth temperature sensor 37 are used to detect the lubricating oil temperature at the inlet of the gas turbine, the lubricating oil temperature at the outlet of the gas turbine lubricating oil chamber, and the lubricating oil temperature of the return oil pipeline in front of the plate heat exchanger 33.

[0048] Other compositions and connection relationships are the same as those in the first specific embodiment.

[0049] Specific embodiment seven: Figure 1 To describe this embodiment, the lubrication system of a gas turbine unit in this embodiment further includes a first liquid level signaler 21 and a second liquid level signaler 22; the first liquid level signaler 21 and the second liquid level signaler 22 are installed on the circulation oil tank 20.

[0050] The first liquid level signaler 21 and the second liquid level signaler 22 are used to ensure an alarm when the liquid level of the gas turbine circulation oil tank 20 is lower than the specified value.

[0051] Other compositions and connection relationships are the same as those in the first specific embodiment.

[0052] Specific embodiment eight: Figure 1Describing this embodiment, the lubrication system of a gas turbine unit in this embodiment further includes a first stop valve 23 and a second stop valve 24, and the first stop valve 23 and the second stop valve 24 are installed on the circulation oil tank 20. Other components and connection relationships are the same as those in the first specific embodiment.

[0053] Specific Embodiment Nine: Combining Figure 1 Describing this embodiment, the lubrication system of a gas turbine unit in this embodiment further includes a first differential pressure signaler 32 and a second differential pressure signaler 40. The first differential pressure signaler 32 is installed on the return oil double filter 31, and the second differential pressure signaler 40 is installed on the inlet oil double filter 39.

[0054] The first differential pressure signaler 32 and the second differential pressure signaler 40 are used to monitor the fouling of the inlet oil double filter 39 and the return oil double filter 31. When the differential pressure reaches the set values of the first differential pressure signaler 32 and the second differential pressure signaler 40, an oil filter fouling alarm is issued.

[0055] Other components and connection relationships are the same as those in the first specific embodiment.

[0056] Specific Embodiment Ten: Combining Figure 1 Describing this embodiment, the lubrication system of a gas turbine unit in this embodiment further includes a first pressure sensor 34 and a second pressure sensor 41. The first pressure sensor 34 is installed on the oil path between the lubricating oil assembly 29 and the plate heat exchanger 33, and the second pressure sensor 41 is installed on the oil path between the inlet oil double oil path 39 and the gas turbine. Other components and connection relationships are the same as those in the first specific embodiment.

[0057] Working Principle

[0058] When the gas turbine is working, the booster pump A of the lubricating oil assembly pumps lubricating oil from the circulation oil tank, and supplies the lubricating oil to the gas turbine bearing components, the lower transmission box and the lubricating oil assembly through the check valve, the inlet oil double filter and the protection oil filter of the lubricating oil assembly to lubricate and cool these components; the used lubricating oil coming out of the front casing of the low-pressure compressor is pumped back by the return pump E of the lubricating oil assembly 29 through the intermediate small oil tank 36, the used lubricating oil coming out of the compressor transition section enters the lower transmission box and is pumped back by the return pump D of the lubricating oil assembly 29, the used lubricating oil coming out of the rear casing of the high-pressure compressor, the low-pressure turbine support ring and the power turbine support ring enters the oil-gas separation tank 18 and is pumped back by the return pump B of the lubricating oil assembly 29, the lubricating oil separated by the small oil-gas separator 5 is pumped back by the return pump C of the lubricating oil assembly 29, and the lubricating oil separated by the static oil-gas separator 1 is pumped back by the return pump F of the lubricating oil assembly 29. The lubricating oil pumped back by the lubricating oil assembly 29 returns to the circulation oil tank 20 through the check valve, the plate heat exchanger 33 and the return oil double filter 31 of the lubricating oil assembly 29.

[0059] The oil-gas mixture from the front casing of the low-pressure compressor, the transition section, and the oil-gas separation tank 20 enters the small oil-gas separator 5, and enters the static oil-gas separator 1 through the first throttle washer 6. The lubricating oil is finally separated from the oil-gas mixture, and the separated air enters the exhaust pipe.

[0060] The above are only the preferred embodiments of the present invention, and do not impose any formal restrictions on the present invention. Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some changes or modifications to equivalent embodiments by using the above-disclosed technical content within the scope of the technical solution of the present invention. However, as long as it does not depart from the content of the technical solution of the present invention, any simple modification, equivalent replacement, and improvement made to the above embodiments within the spirit and principle of the present invention still fall within the protection scope of the technical solution of the present invention.

Claims

1. A lubrication system for a gas turbine unit, characterized in that: The described lubrication system for a gas turbine unit includes a static oil-gas separator (1), a small oil-gas separator (5), an oil-gas separation tank (18), a circulating oil tank (20), an oil lubrication assembly (29), a return double oil filter (31), a plate heat exchanger (33), an intermediate small oil tank (36), an inlet double oil filter (39), a first magnetic chip signaler (12), a second magnetic chip signaler (14), a third magnetic chip signaler (16), a fourth magnetic chip signaler (28), and a fifth magnetic chip signaler (38); The static oil-gas separator (1) is connected to the small oil-gas separator (5), the small oil-gas separator (5) is connected to the oil-gas separation tank (18), the oil-gas separation tank (18) is connected to the oil lubrication assembly (29), the oil-gas separation tank (18) is connected to the gas turbine, the small oil-gas separator (5) is connected to the oil lubrication assembly (29), the oil lubrication assembly (29) is connected to the gas turbine through the intermediate small oil tank (36), the oil lubrication assembly (29) is connected to the return double oil filter (31) through the plate heat exchanger (33), the return double oil filter (31) is connected to the circulating oil tank (20), the inlet double oil filter (39) is connected to the gas turbine, the inlet double oil filter (39) is connected to the circulating oil tank (20), and the inlet double oil filter (39) is connected to the oil lubrication assembly (29); The first magnetic chip signaler (12), the second magnetic chip signaler (14), and the third magnetic chip signaler (16) are installed on the oil path connecting the oil-gas separation tank (18) and the gas turbine, the fourth magnetic chip signaler (28) is installed on the oil path connecting the oil lubrication assembly (29) and the oil-gas separation tank (18), and the fifth magnetic chip signaler (38) is installed on the oil path connecting the intermediate small oil tank (36) and the gas turbine; The described lubrication system for a gas turbine unit further includes a first pressure signaler (2), a second pressure signaler (3), and a third pressure signaler (4); the first pressure signaler (2), the second pressure signaler (3), and the third pressure signaler (4) are installed on the oil path between the inlet double oil filter (39) and the gas turbine.

2. The lubrication system of a gas turbine unit according to claim 1, characterized in that: The described lubrication system for a gas turbine unit further includes a first throttle washer (6), a second throttle washer (42), and a bypass valve (43); the first throttle washer (6) is installed on the oil path between the static oil-gas separator (1) and the small oil-gas separator (5), the bypass valve (43) is installed on the oil path between the inlet double oil filter (39) and the circulating oil tank (20), the second throttle washer (42) is installed on the oil path between the inlet double oil filter (39) and the circulating oil tank (20), and the second throttle washer (42) is located between the bypass valve (43) and the circulating oil tank (20).

3. The lubrication system of a gas turbine unit according to claim 1, characterized in that: The described lubrication system for a gas turbine unit further includes a first protection oil filter (7), a second protection oil filter (8), a third protection oil filter (9), a fourth protection oil filter (10), a fifth protection oil filter (11), a sixth protection oil filter (19), a seventh protection oil filter (26), an eighth protection oil filter (27), and a ninth protection oil filter (30); The first protection oil filter (7), the second protection oil filter (8), the third protection oil filter (9), the fourth protection oil filter (10), and the fifth protection oil filter (11) are installed on the gas turbine. The first protection oil filter (7), the second protection oil filter (8), the third protection oil filter (9), the fourth protection oil filter (10), and the fifth protection oil filter (11) are all connected to the inlet double oil filter (39), and the first protection oil filter (7), the second protection oil filter (8), the third protection oil filter (9), the fourth protection oil filter (10), and the fifth protection oil filter (11) are all connected to the circulating oil tank (20); The sixth protection oil filter (19) and the ninth protection oil filter (30) are installed on the circulating oil tank (20), the seventh protection oil filter (26) and the eighth protection oil filter (27) are installed on the lower transmission box connected to the lubricating oil assembly (29), and the ninth protection oil filter (30) is connected to the lubricating oil assembly (29).

4. The lubrication system of a gas turbine unit according to claim 1, wherein: The lubrication system of the gas turbine unit further includes a first temperature sensor (13), a second temperature sensor (15), a third temperature sensor (17), a fourth temperature sensor (25), a fifth temperature sensor (35), and a sixth temperature sensor (37); The first temperature sensor (13), the second temperature sensor (15), and the third temperature sensor (17) are installed on the oil path where the oil and gas separation tank (18) is connected to the gas turbine. The fourth temperature sensor (25) is installed on the circulating oil tank (20), the fifth temperature sensor (35) is installed on the oil path where the lubricating oil assembly (29) is connected to the plate heat exchanger (33), and the sixth temperature sensor (37) is installed on the oil path where the intermediate small oil tank (36) is connected to the gas turbine.

5. The lubrication system of a gas turbine unit according to claim 1, characterized in that: The lubrication system of the gas turbine unit further includes a first liquid level signaler (21) and a second liquid level signaler (22); The first liquid level signaler (21) and the second liquid level signaler (22) are installed on the circulating oil tank (20).

6. The lubrication system of a gas turbine unit according to claim 1, wherein: The lubrication system of the gas turbine unit further includes a first stop valve (23) and a second stop valve (24), and the first stop valve (23) and the second stop valve (24) are installed on the circulating oil tank (20).

7. The lubrication system of a gas turbine unit according to claim 1, characterized in that: The lubrication system of the gas turbine unit further includes a first differential pressure signaler (32) and a second differential pressure signaler (40). The first differential pressure signaler (32) is installed on the return double oil filter (31), and the second differential pressure signaler (40) is installed on the inlet double oil filter (39).

8. The lubrication system of a gas turbine unit according to claim 1, characterized in that: The lubrication system of the gas turbine unit further includes a first pressure sensor (34) and a second pressure sensor (41). The first pressure sensor (34) is installed on the oil path between the lubricating oil assembly (29) and the plate heat exchanger (33), and the second pressure sensor (41) is installed on the oil path between the inlet double oil filter (39) and the gas turbine.

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