Integrated piping interconnection system and turboprop equipped with such an interconnection system

Abstract

Interconnection system (1) for an aircraft turbomachine, comprising a plate (2) including rigid conduits (C) integral with the plate (2) providing the connection of at least two elements to each other and to at least one inlet and at least one outlet, for oil circulation. Figure for the abstract: [Fig 2]

Description

Title of the invention: Integrated piping interconnection system and turboprop equipped with such an interconnection system. Technical field

[0001] The invention relates to the technical field of aircraft propulsion hydraulic systems, and more particularly, the interconnection of the elements of such systems. Prior art

[0002] Unfaired turboprop engines with variable-pitch blades can be feathered in the event of an in-flight engine failure. A dedicated tank and pump system is therefore installed on the engine, connected by pipes via bypass lines and / or valves.

[0003] In turboprop engines with an unfaired architecture, only a main tank and a GDL (Lubrication Group) were present. Feathering is achieved by counterweights as a blade feathering system.

[0004] However, the new architectures of such turboprop engines require a "feathering" type of operation in which feathering is achieved by independently controlling the pitch angle of each blade. Such feathering occurs during "windmilling" flight phases (flight phases during which the engine is shut down, and the blades are set in motion solely by the movement of air due to the aircraft's glide).

[0005] In order to reduce the mass, volume, and cost of these systems, the counterweights have been removed. However, to maintain the possibility of feathering and feathering operation, it is necessary to integrate a new dedicated system comprising a pump driven by an electric motor and a dedicated reservoir. Lubrication of the RGB (Reduction Gearbox) is also necessary in windmilling to prevent it from seizing, which necessitates the addition of a reservoir and a dedicated electric pump.

[0006] In addition to supporting these new modes of operation, the new architectures require smaller compartments in which these systems are mounted, for reasons of drag and mass.

[0007] The integration of the two pumps, two motors, two tanks as well as the necessary valves and flaps results in an increase in the density of the compartments.

[0008] There is a need for an interconnection system allowing the integration of these additional elements into the allocated volume.

[0009] In addition to the strong constraints presented above, other operating constraints exist to ensure the flagging action:

[0010] 1- Each pump must be located under the corresponding reservoir in order to be supplied due to the gravity of the situation.

[0011] 2- Pressure losses must be reduced by reducing the number and severity bends as well as the length of the pipes.

[0012] 3- The various elements of the flagging circuit must be integrated to the maximum close to each other.

[0013] Similar operating constraints exist to ensure the lubrication of the RGB reduction box.

[0014] Figure [Fig.1] illustrates the current dimensions of a compartment equipped with all the elements for feathering operation during windmilling flight phases.

[0015] The elements include an oil reservoir for the control of the FOT feathering function, an NRV check valve, an SUV shuttle valve, a bypass path for the FPBV feathering function, a ROPT set of oil pressure and temperature sensors for the reduction gearbox and a PCU variable pitch control unit, an FP feathering function pump and an RGBP reduction gearbox pump.

[0016] Each element is connected by at least two discrete conduits running on several levels within the compartment. A specific arrangement must be followed in order to install all the elements and all the conduits connecting them to each other and to the rest of the aircraft.

[0017] It thus appears that the compartment is currently very cluttered. It is difficult, if not impossible, to install the various equipment and pipes while respecting the installation clearances and the minimum bending radii for the pipes.

[0018] The object of the invention is an oil interconnection system allowing a reduction in installation clearances and the number of pipes to be routed between several pieces of equipment. Description of the invention

[0019] The invention relates to an interconnection system of elements of a feathering function for a turbomachine comprising a plate of rigid oil lines attached to the plate ensuring the fluid connection of at least two of said elements to each other and to at least one inlet and at least one outlet, for the circulation of oil.

[0020] The elements may include at least one of an oil reservoir, an oil pump, a valve, a bypass channel, a pressure sensor or a temperature sensor.

[0021] The oil inlet / outlet interfaces of the pumps can be directly connected to the mounting plate via quick-release fasteners or gasket plates

[0022] At least one inlet and at least one outlet of the plate may each incorporate a self-sealing valve.

[0023] The plate can incorporate a system of handling handles and / or hoisting cleats.

[0024] The interconnection system may include a reduction gearbox pump connected by its inlet to the reduction gearbox and by its outlet to an inlet of a shuttle valve, the outlet of the shuttle valve being connected to the reduction gearbox via a set of oil pressure and temperature sensors for the reduction gearbox, another inlet of the shuttle valve being connected to an oil inlet line for supplying oil, a variable pitch control unit connected by an output to an input of a bypass channel of the feathering function, and an input of the variable pitch control unit connected to an output of the bypass channel of the feathering function, another output of the bypass channel of the feathering function being connected to the inlet of the pump of the feathering function via the check valve,An oil reservoir for controlling the feathering function is connected between the outlet of the check valve and the inlet of the feathering function pump, the outlet of the feathering function pump being connected to another inlet of the feathering function bypass path.

[0025] The non-return valve, the shuttle valve and the bypass route for the flagging function can be permanently installed on the plate.

[0026] The oil reservoir for the control of the feathering function, the pump for the feathering function, the oil reservoir for the reduction gearbox backup, the reduction gearbox pump and the set of oil pressure and temperature sensors for the reduction gearbox can be connected to the plate while being fixed securely to the plate.

[0027] The invention also relates to a turbomachine comprising an interconnection system as described above. Brief description of the drawings

[0028] Other objects, features and advantages of the invention will become apparent from the following description, given solely by way of non-limiting example and made with reference to the accompanying drawings in which:

[0029] - Figure [Fig. 1] illustrates the current dimensions of a compartment equipped with all the elements for "feathering" type operation during "windmilling" type flight phases, and

[0030] - Figure [Fig.2] illustrates the interconnection system according to the invention applied to hydraulic lubrication circuits of the reduction gearbox and blade "feathering" mechanism of an aircraft turboprop engine. Detailed description

[0031] To resolve the integration problems of the two systems (reservoirs, pumps, valves, etc.) and the routing of the pipes between these elements, the inventors conceived the idea of ​​designing an interconnection system integrating the pipes and the various components of the schematic diagram (valve, bypass, etc.) onto a plate manufactured using additive manufacturing. This plate also serves as a support for the pumps and reservoir dedicated to the feathering function. For the feathering function, a first reservoir and a second reservoir for backup lubrication of the RGB (Rubber-Based Lubrication) are provided so that these two systems are as independent as possible from the main lubrication circuit. The identified solution allows for a more compact installation.

[0032] This solution is compatible with all pump technologies (vanes, pistons and gears) having radial or axial interfaces.

[0033] The various components such as pumps, valves and sensors interface with the circuit board as easily replaceable modules. The components are rigidly mounted.

[0034] Strainers as well as various pressure, temperature, flow sensors can be installed at the level of the plate.

[0035] These components together with the turntable represent a compact assembly in which inter-component clearances are reduced to the strict minimum.

[0036] The oil inlet / outlet interfaces of the pumps are directly connected to the plate via quick-fixing means or gasket plates.

[0037] The oil inlet / outlet interfaces of the plate incorporate self-sealing valves to facilitate maintenance.

[0038] To facilitate handling and / or maintenance, the plate incorporates a system of handling handles and / or lifting cleats for handling the assembly with a lifting tool.

[0039] The plate can be manufactured by casting, additive manufacturing or any other machining means.

[0040] Figure [Fig.2] illustrates the interconnection system according to the invention applied to the hydraulic lubrication circuits of the RGB reduction box and blade pitching of the feathering function of an aircraft turboprop.

[0041] The interconnection system 1 comprises a plate 2 including rigid conduits C attached to the plate 2 ensuring the connection of at least two elements to each other and to at least one input and to at least one output.

[0042] The elements include an oil reservoir for the control of the FOT feathering function, a pump for the FPASP feathering function, an oil reservoir for the RGB backup, a reduction gearbox pump RGBP, an NRV check valve, an SUV shuttle valve, a bypass path for the FPBV feathering function, a ROPT set of oil pressure and temperature sensors for the reduction gearbox and a PCU variable pitch control unit.

[0043] More specifically, the inlet of the RGBP reduction gearbox pump is connected to a reservoir that collects oil from the RGB reduction gearbox. The outlet of the RGBP reduction gearbox pump is connected to an inlet of the SUV shuttle valve. The outlet of the SUV shuttle valve is connected to the RGB reduction gearbox via the ROPT assembly of oil pressure and temperature sensors for the reduction gearbox.

[0044] The other inlet of the SUV shuttle valve is connected to an oil inlet line allowing for oil supplementation.

[0045] The variable step control unit PCU is connected by its output to an input of the bypass channel of the flagging function FPBV, and by its input to an output of the bypass channel of the flagging function FPBV.

[0046] Another output of the FPBV feathering function bypass path is connected to the FPASP feathering function pump inlet via the NRV check valve. The oil reservoir for controlling the FOT feathering function is connected between the NRV check valve outlet and the FPASP feathering pump inlet.

[0047] The output of the pump of the FPASP flagging function is connected to the other input of the bypass path of the FPBV flagging function.

[0048] Among the elements permanently installed on the plate 2 are the NRV check valve, the SUV shuttle valve and the bypass route of the flagging function FPBV.

[0049] The oil reservoir for the control of the FOT feathering function, the FPASP feathering function pump, the reduction gearbox pump RGBP and the ROPT set of oil pressure and temperature sensors for the reduction gearbox are connected to plate 2 while being fixed securely to plate 2. By fixed securely, we mean a fixing which allows the plate 2 to be manipulated while the elements are fixed, without the latter being able to move.

[0050] The RGB reduction box and the PCU variable pitch control unit are not integrated or fixed permanently to the plate 2. They are therefore connected to the interconnection system 1 via discrete conduits and connection means, such as quick connectors.

Claims

Demands

1. Interconnection system (1) of elements of a feathering function for aircraft turbomachine comprising a plate (2), rigid oil lines (C) integral with the plate (2) providing the fluidic connection of at least two of said elements to each other and to at least one inlet and at least one outlet, for the circulation of oil.

2. Interconnection system (1) according to claim 1, wherein the elements comprise at least one of an oil reservoir, an oil pump, a valve, a bypass path, a pressure sensor or a temperature sensor.

3. Interconnection system (1) according to claim 2, wherein the oil inlet / outlet interfaces of the pumps are directly connected to the plate via quick-fixing means or gasket plates.

4. Interconnection system (1) according to any one of claims 1 to 3, wherein at least one input and at least one output of the plate each incorporate a self-sealing valve.

5. Interconnection system (1) according to any one of claims 1 to 4, wherein the plate incorporates a system of handling handles and / or hoisting cleats for handling by a lifting tool.

6. An interconnection system according to any one of claims 1 to 5, comprising a gearbox pump (RGBP) connected by its inlet to the gearbox (RGB) and by its outlet to an inlet of a shuttle valve (SUV), the outlet of the shuttle valve (SUV) being connected to the gearbox (RGB) via an assembly (ROPT) of oil pressure and temperature sensors for the gearbox, another inlet of the shuttle valve (SUV) being connected to an oil inlet line for supplying oil, a variable pitch control unit (PCU) connected by its output to an input of a feathering function bypass channel (FPBV), and an input of the variable pitch control unit (PCU) connected to an output of the feathering function bypass channel (FPBV), another output of the feathering function bypass channel (FPBV) connected at the inlet of the feathering function pump (FPASP) via the check valve (NRV), an oil reservoir for the control of the feathering function (FOT) being connected between the outlet of the check valve (NRV) and the inlet of the feathering function pump (FPASP), the outlet of the feathering function pump (FPASP) being connected to another inlet of the feathering function bypass route (FPBV).

7. Interconnection system (1) according to claim 6, wherein the non-return valve (NRV), the shuttle valve (SUV) and the bypass path of the feathering function (FPBV) are permanently installed on the plate.

8. Interconnection system (1) according to claim 6 or 7, wherein the oil reservoir for the control of the feathering function (FOT), the pump for the feathering function (FPASP), the oil reservoir for the gearbox backup (RGB), the gearbox pump (RGBP) and the assembly (ROPT) of oil pressure and temperature sensors for the gearbox are connected to the plate (2) while being fixed securely to the plate (2).

9. Aircraft turbomachine comprising an interconnection system (1) according to any one of claims 1 to 8.

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