RU7144U1 - GAS TURBINE ENGINE - Google Patents

Abstract

1. A gas turbine engine with a free turbine of a modular design, consisting of nine main modules: a screw reducer, a central drive, an axial compressor, a turbocompressor, including a centrifugal compressor stage and a compressor turbine, a combustion chamber, a free turbine, an output device, a lower box of motor drives units and the upper box of aircraft drives, characterized in that the modules are assembled independently and in parallel, replacing the module without additional balancing and 2. The engine according to claim 1, characterized in that it has a parking brake that automatically turns on when the rotor speed is reduced to a predetermined value and automatically turns off when the maximum torque value on the propeller shaft held by the brake is exceeded.

Description

GAS TURBINE ENGINE

1, The technical field to which the utility model relates. The scope of the utility model is aviation.

equipment, as well as molset to be used as a drive in power plants.

2. The level of technology

There are similar zurabezhnye engines, both experienced and in development; this is rtm. 322-11 firms of Rody) -Royce, ZDbomeka (England-France) with a power of 2800 hp; PV / -I20 from PrattWhitney Aircraft of Canada (Canada) power 2522 hp

For comparison, the data presented in the following bibliographic materials were used:

1. Foreign aircraft engines TsIAM 1934

2. The main data of foreign turboshaft and turboprop engines, ODAM, release 1980-1985.

3. Express information, TsIAM, issues I980-I985

4. Report of the Research Center. Lewis at a conference in NASA 06/23/62. manuscript of translation, NISCH, 1984

From a comparison of the parameters of analog engines, it can be seen that the TB7-II7C engine is in terms of efficiency at the level of promising engines developed by foreign companies. The specific fuel consumption of the TB7-II7C engine is significantly lower than the specific fuel consumption of any similar experimental or serial domestic or foreign engine.

R02K.ZUOO of the owner.

3. The essence of the utility model

The essence of the inventive utility model is that the assembly of the engine modules is independent and parallel. The design and technology provide for the interchangeability of the modules during the production and operation of separate balancing of the rotors in the composition of the modules, the replacement of the modules without additional balancing of the rotors.

The end module - screw editor - can be replaced without removing the engine from the flying object. The replacement of the remaining modules is carried out in the conditions of airfield technical bases.

The proposed utility model is equipped with a parking brake of the screw, which is switched on automatically (sparingly when the rotor speeds are reduced to preset values.

In addition, if in a braked state due to a sharp change in external factors, the torque on the propeller shaft begins to exceed the moment that the brake holds, then it is automatically released, which prevents the brake from breaking. The specified design of the screw brake compares favorably with this utility model from existing analogues.

4. The list of drawings

Figure 1: Longitudinal section of a gas turbine engine indicating the positions of the structural modules

P03.1 - screw reducer

pos.2 - central drive / pos.Z - axial sound absorber

2. pos. 4 - turbocharger pos. 5 - combustion chamber pos. 6 - free turbine pos. 7 - output device pos. 8 - lower gearbox pos. 9 - upper drive box pos. 10 parking brake Fig. 2, Fig. 3, Fig. 4: General view of the positions included in it detail of pos. II - electromagnet pos. 12 - stopper pos. 13 - spring pos. 14 - cylinder pos. 15 - lever pos. 16 block microswitches pos. 17 - power spring pos. 18 - cylinder pos. 19 - spring pos. 20 - housing pos. 21 - bearing pos. 22 brake drum pos. 23 - roller pos. 24 - tension spring pos. 25 - cam pos. 26 - roller pos. 27 - cam pos. .28 - brake pad of motor units in the aircraft of the parking brake, with indicate and nodes:

1103.29 suspension pos.30 - cover POE.31 piston pos.32 - piston

5. Information confirming the utility model implementation

The gas turbine engine is made according to the scheme:

single shaft sedimentrobesky co-reresor, consisting of five axial and one centrifugal stage;

annular countercurrent combustion chamber;

two-stage axial compressor turbine with four cooled crowns;

a two-stage axial free turbine with the output of the power take-off shaft forward to the coaxial screw gearbox located directly in front of the compressor.

The lower and upper drive boxes are located on the lower and upper folders of the input housing.

Structurally useful model consists of nine main modules:

screw gear, pos. 1;

central drive, pos. 2;

axial bucket compressor, pos. З;

a turbocompressor including a centrifugal compressor stage and a compressor turbine, item 4;

combustion chamber, pos. 5;

free turbine, pos.6;

output device, pos. 7;

lower gearbox of propulsion units, air.Z;

checking box for drives of aircraft units, pos. 9.

The engine is equipped with a parking brake, item 10.

Modular assembly and replacement of gas turbine engine modules can be performed repeatedly without additional balancing, and the modules can be manufactured at different plants.

Thus, the modular design of the gas turbine engine is capable of

improving manufacturability and reducing assembly;

about the production of modules for cooperation;

increase engine life;

increase the levels of operational manufacturability and unsuitability of the engine;

simplification of technical maintenance;

lower operating costs

which in the cost of the life cycle of different engines are (60-70)%,

 parking (pos. 10) is designed to hold the propeller in a locked state when the engine is not running. The brake is mounted on the top drive box and connected to it by peccopoli.

The parking brake (Fig. 2,3,4) consists of two main components: a control unit with brake pads and a brake unit with a brake drum.

7 control room consists of a cover (30) with two cylinders:

FUEL (14) in oil (18), power spring (17), lever (15), roller (23), transmitting rotation to the cam (25), two tightening springs (24), two eccentrics (27), two suspensions (29), two pads (28), with friction pads and rollers (26) glued on them, a stopper (12), a spring (13), a stopper, an electromagnet (II), which controls the position of the stopper.

A DAY for monitoring the position of the parking brake, a microswitch block (16) is installed on the cover.

The braking unit consists of a brake housing (20), square roller bearings (21), a brake drum (22) and a spring (19).

Bearing lubrication is applied for the entire period of operation of the brake.

The parking brake is applied by applying a power spring (17) to the lever (15). The power spring, overcoming friction in the two pistons of the fuel and oil cylinders and the force of the springs (24), tightening the pads (28), rotates the cam (25) through the lever (15). The latter unloads the pads (26) through the rollers (26) and presses them against the surface of the brake drum (22), creating a braking torque on the drive spring (19).

When the engine is started, the pistons (31) and (32) under the action of pressure turn the lever (15) clockwise through the rods, compressing the spring (17) and returning the cam (25) to the at least radius. The coupling springs (24) divert the pads (28) from the working surface of the brake drum (22) to the stop in the eccentric (27), thereby releasing the propeller shaft. c When zvuscu is pulled to toe in half A, the bristle (33) moves upward, releasing the stopper (12), under the top (13) it turns counterclockwise and is installed under the butt end B (32}. Thus, the right side of the engine is under pressure (cavity pressure But it falls) it is shifted by moving the piston (32) down and on to the TojpMosa from the power (G), The brake can only be applied by applying electrical power to the power supply (II), while it is electrically powered, the pusher is up, the spring (G) is compressed, and 12 ) turns right and provides the ability to move The piston (32) is downward. The amplification of the electromagnet (II) is not enough to move the stopper (12) to the right position if (17) is too loose. Therefore, the power supply must be carried out directly in front of the engine wheels. This technical solution has been mastered in servo production and is certified. In the process of implementation of the work to confirm the specified certification basis, a technical result was obtained, giving solutions of which this useful modal is intended.

Claims (2)

1. A gas turbine engine with a free turbine of a modular design, consisting of nine main modules: a screw reducer, a central drive, an axial compressor, a turbocompressor, including a centrifugal compressor stage and a compressor turbine, a combustion chamber, a free turbine, an output device, a lower box of motor drives units and the upper box of aircraft drives, characterized in that the modules are assembled independently and in parallel, replacing the module without additional balancing and.  2. The engine according to claim 1, characterized in that it has a parking brake that automatically turns on when the rotor speed decreases to the set values and automatically turns off when the maximum torque value on the shaft of the propeller held by the brake is exceeded.