RU207097U1 - CYLINDRICAL RING WITH AERODYNAMIC PROFILE FORMING AIRFLOW DIRECTION OF THE SECOND CIRCUIT OF A GAS TURBINE ENGINE - Google Patents

Abstract

The utility model relates to the design of a compressor of a bypass gas turbine engine using technologies for the production of composite products by thermal stamping using additive technology of layer-by-layer growth. mechanical work to drive the external circuit fan, which creates the main draft. An important characteristic of a bypass turbojet engine is the bypass ratio, which implies the ratio of the air volumes passing through the outer and inner loops. In any case, the mixing of the flows of each circuit occurs at the outlet of the nozzle. At present, polymer composite materials are increasingly used in aircraft engine building, which have relatively high mechanical properties at a relatively low specific gravity. Polymer composite materials consist of two main components: (polymer binder (synthetic resin) and fibrous filler (fabric or unidirectional bundle made of carbon, organo - or fiberglass)) The method of thermal stamping includes: - laying a reinforced composite with a thermoplastic binder into a mold; - heating to the melting point of the prepreg thermoplastic polymer; - applying pressure for forming a part; - cooling; - demoulding. The method of thermal stamping can be used to produce only shallow products of approximately constant thickness, the most accurate dimensions with simultaneous or subsequent punching of holes and stitching of products, therefore, for further build-up, you stupov additionally use the method of additive technologies, the combination of these technologies allows avoiding connections with screws, riveting or gluing and reducing the risk of damage to the main part. allowing to simplify the manufacturing process with a decrease in the weight of the structure, due to the implementation of the aerodynamic and structural parts in one piece, by means of the manufacture of an aerodynamic part made of a thermoplastic polymer composite material using thermal stamping technology, followed by the use of an additive technology of layer-by-layer build-up, which makes it possible to reduce the number of additional structural elements using additional fasteners, since each additional fastening connection leads to a weakening of the entire structure tions, especially in the longitudinal direction (i.e. in the direction of the axial load of the fastener), and also significantly increases the mass of the structure, which makes it difficult to use this structure in the aerospace industry. air flow of the second circuit of a gas turbine engine, consisting of structural and aerodynamic parts, while the aerodynamic part is made in the form of interconnected panels, the outer surface of which allows optimizing aerodynamic characteristics. New in the utility model is that each panel is made of thermoplastic polymer composite material by thermal stamping and contains slotted holes, the total area of which ensures the maximum air flow rate at the moment of opening the bypass system of the primary circuit, while the structural part is made along the edges of the inner surface of the panel in the form of protrusions with holes for fasteners using the method of building-up by additive technologies.

Description

The utility model relates to the design of a compressor of a by-pass gas turbine engine using technologies for the production of composite products by thermal stamping using additive technology of layer-by-layer build-up.

A turbojet bypass engine (TJE) with internal and external circuits, in which part of the combustion energy of the fuel supplied to the internal circuit is converted into mechanical work to drive the external circuit fan, which creates the main thrust. An important characteristic of a bypass turbojet engine is the bypass ratio, which implies the ratio of the air volumes passing through the outer and inner loops. In any case, the mixing of the flows of each circuit occurs at the outlet of the nozzle.

Currently, in aircraft engine building, polymer composite materials are increasingly used, which have relatively high mechanical properties with a relatively low specific gravity.

Polymer composite materials consist of two main components: (polymer binder (synthetic resin) and fibrous filler (fabric or unidirectional bundle of carbon, organo - or fiberglass)).

Thermal stamping method includes:

- laying a reinforced composite with a thermoplastic binder into a mold;

- heating to the melting point of the prepreg thermoplastic polymer;

- application of pressure to form the part;

- cooling;

- demoulding.

The method of thermal stamping can be used to produce only shallow products of approximately constant thickness, the most accurate dimensions with simultaneous or subsequent punching of holes and stitching of products, therefore, to further build up protrusions, the method of additive technologies is additionally used, the combination of these technologies allows avoiding connections by screws, riveting or gluing and reducing the risk damage to the main part.

Known two-circuit turbofan engine (RF patent No. 2415287, F02K1 / 64, declared 20.06.2005, published 27.03.2011), containing profiled panels performing the function of direction, orientation and straightening of the air flow of the second circuit.

The main disadvantage of this design is the complexity due to the rotary mechanism, which allows you to rotate around its axes in such a way that they are installed across the jet engine shaft.

Also known is the outer shell of a gas turbine engine fan air duct (RF Patent No. 2462601, IPC F01D 25/24, F02K 3/06, conventional priority 26.07.2007 FR 0705455, published 27.01.2010), consisting of structural and aerodynamic parts, while the aerodynamic part made in the form of interconnected panels, the outer surface of which allows optimizing aerodynamic characteristics.

The disadvantage of the described design is the duration, complexity of the manufacturing process due to additional attached structural elements (lattice frame formed by beams and flanges) containing fasteners with machining (drilling holes), weakening the structure, as well as increasing its weight.

The technical result, which the utility model aims to achieve, consists in creating a design of a cylindrical ring with an aerodynamic profile that forms the direction of the air flow, which makes it possible to simplify the manufacturing process with a decrease in the mass of the structure, due to the implementation of the aerodynamic and structural parts in one piece, by means of the manufacture of an aerodynamic parts made of thermoplastic polymer composite material using the technology of thermoforming with the subsequent use of additive technology of layer-by-layer growth, which makes it possible to reduce the number of additional structural elements using additional fasteners, since each additional fastening connection leads to a weakening of the entire structure, especially in the longitudinal direction (i.e. e in the direction of the axial load of the fastener), and also significantly increases the mass of the structure, which makes it difficult to use this structure in aviation but the space industry.

The technical result is achieved by the fact that a cylindrical ring with an aerodynamic profile that forms the direction of the air flow of the second circuit of a gas turbine engine consisting of structural and aerodynamic parts, while the aerodynamic part is made in the form of interconnected panels, the outer surface of which allows to optimize aerodynamic characteristics.

New in the utility model is that each panel is made of thermoplastic polymer composite material by thermal stamping and contains slotted holes, the total area of which ensures the maximum air flow rate at the moment of opening the primary bypass system, while the structural part is made along the edges of the inner surface of the panel in the form of protrusions with holes for fasteners using the method of building up by additive technologies.

The accompanying drawings show:

fig. 1 - 3-D model of a cylindrical ring with an aerodynamic profile that forms the direction of the air flow of the second circuit of the gas turbine engine;

fig. 2 - three-dimensional model of the outer surface of the panel;

fig. 3 - three-dimensional model of the inner panel.

A cylindrical ring with an aerodynamic profile that forms the direction of the air flow of the second circuit of the gas turbine engine contains a structural part 1 (Fig. 3) and an aerodynamic part 2 (Fig. 1, 2).

In this case, the aerodynamic part 2 (Fig. 1, 2) is made in the form of interconnected panels 3 (Fig. 1, 2, 3), the outer surface 4 (Fig. 1, 2) of which allows you to optimize the aerodynamic characteristics.

Each panel 3 (Fig. 1, 2, 3) is made of a thermoplastic polymer composite material by thermal stamping and contains slotted holes 5 (Fig. 1, 2, 3).

The total area of the slotted holes 5 (Fig. 1, 2, 3) provides the maximum air flow rate at the time of opening the bypass system of the primary circuit.

The structural part 1 (Fig. 3) is made along the edges of the inner surface 6 (Fig. 1, 3) of the panel 3 (Fig. 1, 2, 3) in the form of protrusions 7 (Fig. 3) with holes for fastening elements 8 (Fig. 3) by the method of building up by additive technologies.

Depending on the design of the gas turbine bypass engine, calculate the required number of panels 3 (Fig. 1, 2, 3) to form a cylindrical ring, as well as their geometry, the number of slotted holes 5 (Fig. 1, 2, 3) and their respective throughput maximum air flow rate at the time of bypass.

The required number of panels 3 (Fig. 1, 2, 3) is made of thermoplastic polymer composite material by thermal stamping, followed by building up the structural part 1 (Fig. 3), made in the form of protrusions 7 (Fig. 3) and further machining to make the final the shape of the panel 3 (Fig. 1, 2, 3).

When the engine is operating with the inner and outer contour of the panels 3 (Fig. 1, 2, 3), forming a cylindrical ring, direct the air flow of the second loop into the engine nozzle. When the bypass system is started, the air flow from the first circuit through the slot holes 5 (Figs. 1, 2, 3) enters the second circuit of the engine.

The proposed design of a cylindrical ring with an aerodynamic profile that forms the direction of the air flow makes it possible to simplify the manufacturing process with a decrease in the weight of the structure and to successfully use this design in the design of a compressor of a by-pass engine.

Claims (1)

A cylindrical ring with an aerodynamic profile that forms the direction of the air flow of the second circuit of a gas turbine engine, consisting of structural and aerodynamic parts, while the aerodynamic part is made in the form of interconnected panels, the outer surface of which allows optimizing aerodynamic characteristics, characterized in that each panel is made of thermoplastic polymer composite material by thermal stamping and contains slotted holes, the total area of which ensures the maximum air flow rate at the moment of opening the primary bypass system, while the structural part is made along the edges of the inner surface of the panel in the form of protrusions with holes for fasteners by adding additive technologies.

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