CN212646090U

CN212646090U - Fuel oil system, test bench, gas turbine engine and fuel oil main pipe

Info

Publication number: CN212646090U
Application number: CN202021221807.5U
Authority: CN
Inventors: 董干; 肖阳; 张译元; 何敏; 林阳; 孟刚; 袁逸人; 何梦杰
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2020-06-28
Filing date: 2020-06-28
Publication date: 2021-03-02
Anticipated expiration: 2030-06-28

Abstract

The utility model relates to a fuel oil system, test bench, gas turbine engine and fuel mother pipe. The fuel system comprises an oil pump, a fuel oil main pipe, a plurality of oil conveying oil ways and an oil return oil way. The oil pump is used for pumping fuel oil from an oil tank and inputting the fuel oil into the fuel oil main pipe, and the oil return circuit is arranged from the fuel oil main pipe to the oil tank; the plurality of oil delivery paths extend from the fuel oil header to a combustion chamber of the gas turbine engine. The fuel system has the advantages of low cost, simplicity in control and the like.

Description

Fuel oil system, test bench, gas turbine engine and fuel oil main pipe

Technical Field

The utility model belongs to the gas turbine engine field especially relates to a fuel oil system, test bench, gas turbine engine and female pipe of fuel.

Background

Fuel systems (fuel skid/system) refer to a combination of electromechanical devices that pressurize fuel in a fuel tank by a pumping action of an oil pump, transport the fuel through a pipeline, supply the fuel to a target device under the action of a fuel main and/or a regulating valve and/or a switching valve, and regulate the flow and pressure of the supplied fuel. A fuel manifold (header) is disposed downstream of the fuel pump in the fuel system and is used to store high pressure fuel and to continue to supply fuel to the reservoir structure downstream. In a gas turbine engine, such as a turbofan engine development stage, a shaping production stage and a factory returning and maintenance stage, a large number of tests are required to be carried out on a fuel nozzle and a main pipe which are important parts of a combustion chamber, test parameter information is obtained, and a special fuel supply system is required to be designed to meet the fuel supply requirements of the fuel nozzle and the main pipe test piece. With the development of aircraft engines, especially the continuous innovation of turbofan engines with large bypass ratio, the oil supply technology of combustion chambers (fuel main pipes/nozzles) is more and more complex, which is represented by increased oil passages, increased flow and increased difficulty in control and regulation.

In the prior art, the fuel system structure of the combustion chamber test bench mainly has two kinds:

in the first scheme, for example, as shown in fig. 1, a constant speed pump is used for each of a plurality of oil delivery lines, and the downstream of each oil delivery line is matched with a regulating valve and an oil return branch to realize the oil supply flow regulation of the oil delivery line, as shown in fig. 1, the first fuel system 102 comprises three

oil delivery lines

1021, 1022 and 1023, and fuel in a fuel tank 300 is pumped into a test piece 400, namely a combustion chamber of a gas turbine engine, through the

constant speed pumps

14, 15 and 16 respectively. The

oil delivery passages

1021, 1022, 1023 are respectively provided with

oil return passages

1024, 1025, 1026 correspondingly. The

oil delivery paths

1021, 1022 and 1023 are respectively provided with regulating valves 17, 18 and 19,

flow meters

23, 24 and 25 and

pressure sensors

26, 27 and 28 to regulate oil supply pressure and/or oil supply flow, and the

oil return paths

1024, 1025 and 1026 are respectively provided with oil return regulating valves 20, 21 and 22, and the feedback control process comprises the steps that the

pressure sensors

26, 27 and 28 respectively provide pressure feedback of the

oil delivery paths

1024, 1025 and 1026 to a control system, and the oil return regulating valves 20, 21 and 22 of the

oil return paths

1024, 1025 and 1026 corresponding to each oil delivery path and the regulating valves 17, 18 and 19 of each oil delivery path are jointly regulated to obtain specified inlet pressure parameters.

For example, as shown in fig. 2, for each of the plurality of oil transportation paths, a variable frequency pump is used, and the downstream of the variable frequency pump is matched with a regulating valve to directly regulate the oil supply flow of the path. As shown in fig. 2, the second fuel system 103 includes three

fuel delivery lines

1031, 1032, 1033, which draw the fuel in the fuel tank 300 to the test piece 400, i.e., the combustion chamber of the gas turbine engine, by the

inverter pumps

29, 30, 31, respectively, and the

fuel delivery lines

1031, 1032, 1033 have the

control valves

32, 33, 34, the

flow meters

35, 36, 37, and the

pressure sensors

38, 39, 40, respectively, to adjust the supply pressure and/or the supply flow rate, and thus, since the inverter pumps are used, there is no need to provide a return line. The feedback control process comprises the steps that the

pressure sensors

38, 39 and 40 provide feedback of oil

delivery oil paths

1031, 1032 and 1033 to the control system, the rotating speeds of the

variable frequency pumps

29, 30 and 31 are changed, the oil supply quantity is further changed, and the specified inlet pressure parameter is obtained.

However, in the first scheme, more oil pumps and oil return passages need to be arranged, so that the equipment cost is increased, and the complexity and the control difficulty of the system are increased; in the second scheme, a plurality of variable frequency pumps are required to be arranged, the cost is high, and when the number of oil delivery oil ways is large, the cost for performing the test by adopting the second scheme is high.

Accordingly, there is a need in the art for a low cost, simple to control fuel system for use in a test rig of a gas turbine engine combustor, even in the combustor of an actual gas turbine engine.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a fuel oil system with low costs, control is simple, the operation is reliable and stable.

The utility model aims at providing a test bench.

An object of the utility model is to provide a gas turbine engine.

The utility model aims at providing a fuel main pipe.

A fuel system according to one aspect of the present invention includes an oil pump; a fuel oil main pipe; a plurality of oil delivery paths; an oil return path; the oil pump is used for pumping fuel oil from an oil tank and inputting the fuel oil into the fuel oil main pipe, and the oil return circuit is arranged from the fuel oil main pipe to the oil tank; the plurality of oil delivery paths extend from the fuel oil header to a combustion chamber of the gas turbine engine.

In one or more embodiments of the fuel system, the fuel rail includes: the fuel inlet is positioned on one side of the fuel main pipe and communicated with the oil pump; the fuel oil outlets are positioned on the other side of the fuel oil main pipe and communicated with the plurality of fuel oil conveying oil ways; and the oil return outlet is positioned at one end of the fuel oil main pipe and is communicated with the oil return oil way.

In one or more embodiments of the fuel system, the fuel rail includes an internal cavity that communicates with the fuel inlet, the fuel delivery outlet, and the return outlet.

In one or more embodiments of the fuel system, the fuel system further comprises a surge tank for stabilizing the fuel pressure within the fuel rail; the fuel oil main pipe further comprises a pressure stabilizing interface which is positioned at the other end of the fuel oil main pipe and communicated with the inner cavity.

In one or more embodiments of the fuel system, the fuel main pipe is cylindrical, the inner cavity is a passage which traverses the cylindrical shape, two ends of the passage are respectively communicated with the oil return outlet and the pressure stabilizing interface, and the side part of the passage is respectively communicated with the fuel inlet and the fuel delivery outlet.

In one or more embodiments of the fuel system, each of the fuel delivery lines includes a regulator valve, and a pressure sensor and/or a flow meter; the fuel oil main pipe further comprises a pressure measuring point, and the pressure measuring point is communicated with the channel at the side part of the channel.

In one or more embodiments of the fuel system, the oil pumps are constant speed pumps, and the number of the oil pumps is at most two.

According to an aspect of the present invention, a test rig for testing a gas turbine engine combustor comprises a fuel system as described in any one of the above.

A gas turbine engine according to an aspect of the present invention comprises a combustion chamber, and a fuel system as described in any one of the above for supplying fuel to the combustion chamber.

The utility model discloses a fuel oil main pipe according to an aspect of the utility model, which is used for a fuel oil system and comprises a fuel oil inlet, wherein the fuel oil inlet is used for communicating with an oil pump of the fuel oil system; the fuel outlets are used for communicating with a plurality of fuel delivery oil ways of the fuel system; and the oil return outlet is used for communicating an oil return oil way of the fuel system.

The utility model has the advantages that the combination of the fuel oil main pipe and the oil pump is used as the oil supply power device of the fuel oil system, and the oil supply pressure at the front ends of a plurality of oil transportation oil paths is unified; meanwhile, the oil return of the fuel system can be realized by only one oil return oil way of a plurality of oil delivery oil ways, and a plurality of oil return oil ways corresponding to the plurality of oil delivery oil ways or a variable frequency pump are not needed in the prior art, so that the structure of the fuel system is simplified, the equipment cost and the control difficulty of the fuel system are reduced, the cost and the system control difficulty of a test bench or a gas turbine engine are reduced, and the reliability of the fuel system is improved.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which like reference numerals refer to like features throughout, and in which:

fig. 1 shows a prior art fuel system solution.

Fig. 2 shows yet another prior art fuel system arrangement.

FIG. 3 is a schematic structural diagram of a fuel system according to an embodiment.

Fig. 4 is a schematic structural diagram of a fuel header pipe according to an embodiment.

Fig. 5A to 5E are schematic structural views of five angles of a fuel header pipe according to an embodiment.

Fig. 6A and 6B are cross-sectional structural views of fig. 5B and 5E, respectively.

Detailed Description

The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and are not intended to limit the scope of the present invention.

Furthermore, references to "one embodiment," "an embodiment," and/or "some embodiments" mean a particular feature, structure, or characteristic described in connection with at least one embodiment of the application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one or more embodiments" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.

Referring to fig. 3, the fuel system 100 includes a pump, a fuel rail, a plurality of fuel delivery lines, and a return line. Oil pump 1, 2 are invariable speed pump, set up the aim at of two oil pumps, and an oil pump can be in high pressure interval, and another oil pump can be in low pressure interval, adopts the pump that two pressure intervals are different, compares in adopting and satisfies the constant speed pump that high pressure distinguished and low pressure interval simultaneously and is changeed in the control, and control response is more rapid. However, it can be understood that a single oil pump can be adopted, so that the cost can be saved, the oil pump with larger oil supply displacement is selected, the total oil supply flow requirement of each oil path is met, and the cost change caused by the quantity of the oil pumps is far larger than the cost change caused by the capacity of the oil pumps. For example, the oil pump with the displacement difference of 10 times is used as the reference, and the price is generally within 1.5 times. Therefore, the cost can be greatly reduced by reducing the number of the oil pumps. In general, the requirements of test piece 400 for the fuel system are generally met by using at most two constant speed pumps. Compared with the prior art that each oil delivery oil way needs to be provided with a constant rotating speed pump or a variable frequency pump, the cost of the fuel system is reduced, and the structure of the fuel system is simplified, so that the control algorithm requirement of a corresponding control system of the fuel system is reduced.

The fuel flows through a path in which the constant speed fuel pumps 1, 2 pump fuel from the fuel tank 300 to the fuel rail 1000, the fuel rail 1000 returns fuel that needs to be returned to the fuel tank 300 through the return line 1004 to maintain the pressure in the fuel rail 1000, and the return line 1004 may be specifically configured to have a return regulator valve 6 to control the return pressure to control the pressure in the fuel rail 1000. After the fuel reaches the fuel rail 1000, the

fuel lines

1001, 1002, 1003 extend from said fuel rail 1000 to the test piece 400 of the test stand, i.e. the combustion chamber of the gas turbine engine.

The

fuel delivery lines

1001, 1002, 1003 may respectively have regulating valves 3, 4, 5,

flow meters

7, 8, 9 and

pressure sensors

10, 11, 12 to adjust the fuel supply pressure and/or the fuel supply flow, and the specific feedback control may be that, since the fuel delivery lines have the common pump source (combined pump source of the fuel pump and the fuel main)

pressure sensors

10, 11, 12 to provide the

fuel delivery lines

1001, 1002, 1003 with feedback to the control system, the return oil line 1004 connected through the fuel main 1000 returns the regulating valve 6, and combines with the regulating valves 3, 4, 5 of the

fuel delivery lines

1001, 1002, 1003 to work together, so as to obtain the specified inlet pressure parameter, thereby reducing the control and regulation of the fuel pump and the return oil, making the fuel system 100 easy to control, and improving the reliability of the operation of the fuel system 100, compared with the prior art scheme 1.

The oil supply system 100 with the fuel oil main pipe 1000 is arranged in the test bed, and has the advantages that the fuel oil main pipe and the oil pump are combined to serve as an oil supply power device of the fuel oil system, and oil supply pressures at the front ends of a plurality of oil conveying oil ways are unified; meanwhile, the oil return of the fuel system can be realized by only one oil return oil way of a plurality of oil delivery oil ways. The oil pump, the fuel oil main pipe and the oil return oil way are skillfully combined to serve as a common oil source of all oil ways, the limitation of the oil delivery oil way on the number of the oil pumps is eliminated, multiple oil return oil ways corresponding to multiple oil delivery oil ways or variable frequency pumps are not needed in the prior art, the structure of the fuel oil system is simplified, the equipment cost and the control difficulty of the fuel oil system are reduced, the cost and the system control difficulty of a test bench or a gas turbine engine are reduced, and the reliability of the fuel oil system is improved.

Referring to fig. 3-6B, in one or more embodiments, the specific configuration of fuel rail 1000 includes a fuel inlet 1006,

fuel delivery outlets

1007, 1008, 1009, and an oil outlet 1010. The fuel inlet 1006 is located on one side of the fuel manifold 1000, and the fuel inlet 1006 communicates with the constant speed oil pumps 1, 2 of the fuel system 100. The

oil delivery outlets

1007, 1008 and 1009 are positioned on the other side of the fuel oil main pipe 1000 and are communicated with oil

delivery oil ways

1001, 1002 and 1003. As shown in fig. 4, the fuel header 1000 may have a rectangular parallelepiped cylindrical structure, as shown in fig. 5A, with the fuel inlet 1006 located on the left side, as shown in fig. 5B, and the

fuel outlet

1007, 1008, 1009 located on the right side. As shown in fig. 5D, the return outlet 1010 is located at one end of the fuel header 1000 and communicates with the return oil path 1004 of the fuel system 100, and the return outlet 1010 is located at the rear end of the fuel header 1000. The fuel oil main pipe with the structure is simple in structure, easy to process and easy to arrange in the structure of a test bench and a gas turbine engine. As shown in fig. 6A and 6B, the fuel rail 1000 may further include an inner cavity 1011, the inner cavity 1011 is connected to the fuel inlet 1006, the

fuel delivery outlets

1007, 1008 and 1009 and the return outlet 1010, respectively, and in the fuel rail 1000 having a cylindrical structure, the inner cavity 1011 may be a passage crossing the fuel rail 1000. Referring to fig. 3, in some embodiments, the fuel system 100 may further include a pressure stabilizing tank 1005, which is used for pressure stabilizing and energy storage and is capable of cooperating with the oil return line 1004 to stabilize the fuel pressure in the fuel main pipe 1000, as shown in fig. 5C, the fuel main pipe 1000 correspondingly further includes a pressure stabilizing interface 1012 located at the other end of the fuel main pipe 1000, the pressure stabilizing interface 1012 is also communicated with the inner cavity 1011, as shown in fig. 5C, 5D, and fig. 6A and 6B, the pressure stabilizing interface 1012 and the oil return interface 1010 are respectively located at the front and rear ends of the inner cavity 1011 of the channel structure and are communicated with the inner cavity 1011, and the fuel inlet 1006, the

fuel delivery outlet

1007, 1008 and 1009 are located at the side of the inner cavity 1011 and are communicated with the inner cavity 1011, which may make the fuel main pipe 1000 compact. The shape of the channel may be cylindrical. The fuel rail 1000 described above is in the shape of a rectangular parallelepiped, and the inner cavity 1011 is in the shape of a cylinder, but not limited thereto, for example, the fuel rail 1000 may be in the shape of a cylinder, and the inner cavity 1011 may be in the shape of a rectangular parallelepiped. In addition, the fuel rail 1000 may be generally made of stainless steel.

With continued reference to fig. 4, 5E and 6B, the fuel system further includes a pressure sensor 13 directly connected to the fuel rail 1000, and the fuel rail 1000 further includes a pressure measurement point 1013, the pressure measurement point 1013 is located at a side of the inner cavity 1011 and communicates with the inner cavity 1011 to directly monitor the fuel pressure of the fuel rail 1000, so that the pressure of the fuel rail 1000 is directly fed back to the control system to more accurately monitor and control the fuel supply pressure of the fuel system 100.

It will be appreciated by those skilled in the art that the fuel supply system described in the above embodiments can be applied to both testing of the combustor of a gas turbine engine and to the actual configuration of a gas turbine engine for supplying fuel to the combustor.

It will be appreciated by those skilled in the art that the key components of the fuel system 100 described in the above embodiments may be formed separately from the fuel rail 1000, and that the fuel rail 1000 includes a fuel inlet 1006 for communicating with the fuel pumps 1, 2 of the fuel system 100; the fuel system also comprises a plurality of

fuel delivery outlets

1007, 1008 and 1009 which are respectively used for communicating fuel

delivery oil ways

1001, 1002 and 1003 of the fuel system 100; and the oil return outlet 1010 is used for communicating with the oil return path 1004 of the fuel system 100.

As can be seen from the above, the fuel system, the test bed and the gas turbine engine introduced by the above embodiment have the beneficial effects that the fuel main pipe and the oil pump are combined to serve as an oil supply power device of the fuel system, and the oil supply pressures at the front ends of a plurality of oil delivery oil paths are unified; meanwhile, the oil return of the fuel system can be realized by only one oil return oil way of a plurality of oil delivery oil ways, and a plurality of oil return oil ways corresponding to the plurality of oil delivery oil ways or a variable frequency pump are not needed in the prior art, so that the structure of the fuel system is simplified, the equipment cost and the control difficulty of the fuel system are reduced, the cost and the system control difficulty of a test bench or a gas turbine engine are reduced, and the reliability of the fuel system is improved.

Although the present invention has been described with reference to the above embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.

Claims

1. A fuel system for a gas turbine engine combustor, the fuel system comprising:

an oil pump;

a fuel oil main pipe;

a plurality of oil delivery paths;

an oil return path;

the oil pump is used for pumping fuel oil from an oil tank and inputting the fuel oil into the fuel oil main pipe, and the oil return circuit is arranged from the fuel oil main pipe to the oil tank; the plurality of oil delivery paths extend from the fuel oil header to a combustion chamber of the gas turbine engine.

2. The fuel system as recited in claim 1, wherein said fuel rail comprises:

the fuel inlet is positioned on one side of the fuel main pipe and communicated with the oil pump;

the oil delivery outlets are positioned on the other side of the fuel oil main pipe and communicated with the oil delivery oil ways;

and the oil return outlet is positioned at one end of the fuel oil main pipe and is communicated with the oil return oil way.

3. The fuel system as recited in claim 2, wherein said fuel rail includes an interior chamber communicating with said fuel inlet, said fuel delivery outlet, and said return outlet.

4. The fuel system as recited in claim 3, further comprising a surge tank for stabilizing fuel pressure within said fuel rail; the fuel oil main pipe further comprises a pressure stabilizing interface which is positioned at the other end of the fuel oil main pipe and communicated with the inner cavity.

5. The fuel system as recited in claim 4, wherein said fuel rail is cylindrical, said internal cavity is a passage extending across said cylindrical, two ends of said passage are respectively connected to said return port and said pressure-stabilizing port, and side portions of said passage are respectively connected to said fuel inlet and said delivery port.

6. The fuel system as recited in claim 5, wherein each of said fuel delivery circuits includes a regulator valve, and a pressure sensor and/or a flow meter; the fuel oil main pipe further comprises a pressure measuring point, and the pressure measuring point is communicated with the channel at the side part of the channel.

7. The fuel system as recited in claim 6, wherein said oil pumps are constant speed pumps, and said number of said oil pumps is at most two.

8. A test rig for testing a gas turbine engine combustor, comprising a fuel system according to any one of claims 1-7.

9. A gas turbine engine comprising a combustion chamber and a fuel system according to any one of claims 1-7 for supplying fuel to said combustion chamber.

10. A fuel oil main pipe for a fuel oil system is characterized by comprising

The fuel inlet is used for being communicated with an oil pump of the fuel system;

the oil delivery outlets are used for being communicated with a plurality of oil delivery oil ways of the fuel system;

and the oil return outlet is used for communicating an oil return oil way of the fuel system.