Interconnection system with integrated pipes and turboprop engine provided with such an interconnection system

Abstract

Disclosed is an interconnection system (1) for an aircraft turbine engine, comprising a plate (2) that comprises rigid conduits (C) secured to the plate (2) and connecting at least two elements to one another and to at least one inlet and to at least one outlet, in order to allow oil to circulate.

Description

[0001] DESCRIPTION

[0002] TITLE: Integrated piping interconnection system and turboprop engine equipped with such an interconnection system

[0003] technical field

[0004] The invention relates technically to aircraft propulsion hydraulic systems, and more particularly to the interconnection of elements of such systems.

[0005] Previous techniques

[0006] 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 channels and / or valves.

[0007] In turboprop engines with an unfaired design, only a main fuel tank and a lubrication system were present. Feathering was achieved using counterweights as a blade feathering system.

[0008] 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. This 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 airflow caused by the aircraft's glide).

[0009] 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, a new dedicated system is required, including a pump driven by an electric motor and a dedicated reservoir. Lubrication of the RGB (Reduction Gearbox) is also necessary in windmilling to prevent seizing, which necessitates the addition of a reservoir and a dedicated electric pump.

[0010] 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.

[0011] The integration of the two pumps, two motors, two tanks as well as the necessary valves and flaps results in an increase in compartment density.

[0012] There is a need for an interconnection system that allows these additional elements to be integrated into the allocated volume.

[0013] In addition to the significant constraints presented above, other operational constraints exist to ensure the flagging action:

[0014] 1 - Each pump must be located under its corresponding reservoir to ensure it is gravity-fed in all situations.

[0015] 2- Pressure losses must be reduced by reducing the number and severity of bends as well as the length of pipes.

[0016] 3- The different elements of the flagging circuit must be integrated as close as possible to each other.

[0017] Similar operating constraints exist to ensure lubrication of the RGB reduction box.

[0018] Figure [Eig 1] illustrates the current size of a compartment equipped with all the elements for feathering operation during windmilling flight phases.

[0019] The components include an oil reservoir for the LOT feathering function control, an NRV check valve, an SUV shuttle valve, an EPBV feathering function bypass, a ROPT set of oil pressure and temperature sensors for the reduction gearbox and a PCU variable pitch control unit, a PP feathering function pump, and an RGBP reduction gearbox pump. Each component is connected by at least two discrete lines running on multiple levels within the compartment. A specific layout must be followed to allow for the installation of all components and the lines connecting them to each other and to the rest of the aircraft.

[0020] It 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 bend radii for the pipes.

[0021] 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.

[0022] Description of the invention

[0023] 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.

[0024] The components may include at least one of an oil reservoir, an oil pump, a valve, a bypass channel, a pressure sensor or a temperature sensor.

[0025] The pumps' oil inlet / outlet interfaces can be directly connected to the mounting plate via quick-release fasteners or gasket plates.

[0026] At least one input and at least one output of the circuit board can each incorporate a self-sealing valve.

[0027] The platform can incorporate a system of handling handles and / or hoisting cleats.

[0028] 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 to provide oil supplementation, 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.

[0029] The non-return valve, the shuttle valve and the bypass path for the feathering function can be permanently installed on the plate.

[0030] 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.

[0031] The invention also relates to a turbomachine comprising an interconnection system as described above.

[0032] Brief description of the drawings

[0033] Other objects, features and advantages of the invention will become apparent from the following description, given solely by way of non-limiting example and with reference to the accompanying drawings in which: - 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

[0034] - Figure [Fig 2] illustrates the interconnection system according to the invention applied to the hydraulic lubrication circuits of the reduction gearbox and the feathering blade shim of an aircraft turboprop.

[0035] Detailed description

[0036] To resolve the integration issues between the two systems (reservoirs, pumps, valves, etc.) and the routing of the piping between these components, the inventors conceived an interconnection system integrating the piping 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) system are planned, ensuring these two systems are as independent as possible from the main lubrication circuit. The identified solution allows for a more compact installation.

[0037] This solution is compatible with all pump technologies (vanes, pistons and gears) with radial or axial interfaces.

[0038] The various components, such as pumps, valves, and sensors, interface with the circuit board like easily replaceable modules. The components are rigidly mounted.

[0039] Strainers as well as various pressure, temperature, and flow sensors can be installed on the plate.

[0040] These components and the mounting plate form a compact assembly in which inter-component clearances are reduced to an absolute minimum. The pumps' oil inlet / outlet interfaces are directly connected to the mounting plate via quick-release fasteners or gasketed plates.

[0041] The oil inlet / outlet interfaces of the circuit board incorporate self-sealing valves to facilitate maintenance.

[0042] 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.

[0043] The base plate can be manufactured by casting, additive manufacturing or any other machining method.

[0044] Figure [Fig 2] illustrates the interconnection system according to the invention applied to the hydraulic lubrication circuits of the RGB reduction gearbox and blade pitching of the feathering function of an aircraft turboprop.

[0045] The interconnection system 1 includes a plate 2 comprising 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 at least one output.

[0046] The components include an oil reservoir for the FOT feathering function control, an FPASP feathering function pump, an oil reservoir for the RGB backup, an RGBP gearbox pump, an NRV check valve, an SUV shuttle valve, an FPBV feathering function bypass path, a ROPT set of oil pressure and temperature sensors for the gearbox, and a PCU variable pitch control unit.

[0047] 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 one 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. The other inlet of the SUV shuttle valve is connected to an oil inlet line for oil top-up.

[0048] The variable pitch control unit (PCU) is connected via its output to an input of the FPBV flagging function bypass channel, and via its input to an output of the FPBV flagging function bypass channel.

[0049] Another output of the FPBV feathering function bypass is connected to the FPASP feathering function pump inlet via the NRV check valve. The oil reservoir for the FOT feathering function control is connected between the NRV check valve outlet and the FPASP feathering pump inlet.

[0050] The pump output of the FPASP flagging function is connected to the other input of the FPBV flagging function bypass path.

[0051] Among the elements permanently installed on plate 2 are the NRV check valve, the SUV shuttle valve and the FPBV flagging function bypass.

[0052] The oil reservoir for the control of the FOT feathering function, the pump for the FPASP feathering function, the RGBP reduction gearbox pump and the ROPT assembly 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.

[0053] 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 couplings.

Claims

DEMANDS 1. Interconnection system (1) of elements of a feathering function for aircraft turbomachine comprising a plate (2), elements of a feathering function for aircraft turbomachine, rigid oil lines (C) attached to the plate (2) ensuring 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 a set (ROPT) of oil pressure and temperature sensors for the gearbox, another inlet of the shuttle valve (SUV) being connected to an oil supply line for providing oil top-up, and a variable pitch control unit (PCU) connected by its output to an input of a function feathering bypass (FPBV) channel, and a variable pitch control unit (PCU) input connected to an output of the function feathering bypass (FPBV) channel, another output of the function feathering bypass (FPBV) channel connected to the input of the function feathering pump (FPASP) via the check valve (NRV), an oil reservoir for the control of the function feathering (FOT) being connected between the output of the check valve (NRV) and the input of the function feathering pump (FPASP), the output of the function feathering pump (FPASP) being connected to another input of the function feathering bypass (FPBV) channel.

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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