RU27646U1 - Compensator GTU - Google Patents

Description

GTU Compensator

F02C 7/20 F16L51 / 02

The inventive utility model relates to mechanical engineering and can be used to create stationary and transport gas turbine units (GTU).

Lens and bellows expansion joints are known (Ovchinnikov I.N., Ovchinnikov E.I. Ship systems and pipelines. L., Shipbuilding, 1988, p. 65), installed directly behind the diffuser outlet of the gas turbine and designed to reduce the mechanical forces arising due to thermal expansion of parts and components of a gas turbine engine and affecting, in particular, its body. At high gas temperatures typical of modern gas turbine engines, these efforts, in the absence of thermal compensation, can lead to depressurization of flange connections on its casing, warpage, abnormal displacement of the casing relative to the turbine rotor and, as a result, an accident.

For energy gas turbines even of relatively low power (up to 10 MW), the thermal displacements perceived by gas compensators and their overall dimensions are large. The latter is due to the significant volumetric flow rates of temperature-sensitive gases moving through the compensator.

the kinetic energy of a high-speed gas stream into the potential pressure energy needed to move the gas through heat-exchange equipment located in the gas duct and release gas into the atmosphere.

For high efficiency of the energy conversion process, an uninterrupted gas flow in the diffuser must be ensured. The latter is possible at small opening angles of the diffuser, and therefore with a larger length.

All this contributes to an increase in the longitudinal dimensions of the diffuser and gas turbine in general.

The closest technical solution is the design of the Titan-130 engine manufactured by Solar (International Turbomachinery, November / December, 2001, Vol. 42, No. 7 p.19), in which the compensator contains a thermoelastic corrugated shell mounted between the inlet and outlet nozzles, an internal a guide shell mounted on the inlet pipe and placed in the internal cavity of the compensator forming the end section of the diffuser of the gas turbine engine, a shell made in the form of a truncated cone, the base of which is directed in the direction of movement gas flow, the ribs attached to the inlet.

Placing the end portion of the diffuser in the cavity of the compensator made it possible to reduce the longitudinal dimensions of the engine without compromising its reliability. However, when using this compensator for a highly economical gas turbine with heat recovery in heat exchangers located in the exhaust duct, it is necessary to restructure the gas velocity field for supplying heat exchangers to the gas duct, which, in

this design, can be achieved due to the significant lengthening of the adapter pipe, and therefore the entire gas turbine.

A useful model solves the problem of increasing the compactness of gas turbines with heat recovery of exhaust gases.

To solve the problem, in the compensator of a gas turbine installation containing a thermoelastic corrugated shell mounted between the inlet and outlet pipes, an inner guide shell fixed at one end to the inlet pipe and located in its inner cavity forming the end section of the diffuser of the gas turbine engine, connected by ribs to the inlet pipe, the specified shell forming the end section of the diffuser of the gas turbine engine is made in the form of a cone, truncated whose tire is directed towards the movement of the gas stream.

Moreover, the thermoelastic corrugated shell may be made of two or more sections interconnected by bearing shells.

With this design of the compensator, there is no need for significant restructuring of the gas stream when it is directed to the heat exchanger path, since, in contrast to the prototype, the vectors of the outlet gas flow velocities are directed to the axis of the transition pipe, which helps to reduce the length of the vortex zone behind the cone made in the form of a cone , the truncated apex of which is directed towards the movement of the gas stream, and the alignment of the velocity field along the cross section of the pipe, which significantly reduces the length of the transition pipe between gas turbine engine and this heat exchanger. In addition, the presence of internal

cavity compensator ribs having a streamlined shape, in the proposed design, helps to straighten the swirling gas flow moving in the diffuser. In this case, there is a decrease in hydraulic losses in the diffuser, an increase in the efficiency of the energy conversion process in it.

.The drawing shows an example of the design of a gas turbine expansion joint with a thermoelastic corrugated shell made of two sections, a longitudinal section.

The compensator (Fig.) Contains a thermoelastic corrugated shell 1, installed between the input 2 and output 3 pipes. In this example, the thermoelastic corrugated shell 1 is made of two sections connected by a corresponding supporting shell 4.

To reduce hydraulic resistance, a guide shell 5 is placed inside the corrugated shell 1, fixed at one end on the inner surface of the inlet pipe 2. In the case of thermoelastic corrugated shell 1 of two sections, the guide shell 5 can also be made of two parts. In this case, the second part is fixed on the bearing shell 4.

In the inner cavity of the compensator, a shell 6 is formed that forms the end section of the diffuser of the gas turbine engine, made in the form of a cone, the truncated apex of which is directed towards the gas flow. The shell 6 is attached to the inlet pipe 2 by ribs 7 having a streamlined shape.

engine and output communications from sensors monitoring and diagnostics of its components and parts.

The device operates as follows.

The gas stream enters the diffuser channel formed by the inner walls of the inlet pipe 2, the guide shell 5, the outlet pipe 3 and the outer wall of the shell 6. In the channel, the kinetic energy of the gas stream is converted into potential pressure energy, which, when forming the end section of the diffuser of the gas turbine engine shell 6 in the form of a cone, a truncated apex of which is directed towards the movement of the gas stream, is implemented with high efficiency due to a decrease in hydraulic Eph energy provided by the ribs 7.

At the same time, thermal displacements associated with changes in the temperature of both the gas turbine engine itself and the gas ducts, ducts, pipes and heat exchangers of the gas turbine are perceived by the thermoelastic corrugated shell 1 of the compensator, causing a change in its length, practically eliminating the force acting on the body of the gas turbine engine, and, thereby eliminating the depressurization of the flanges and the displacement of the motor housing relative to the rotor, ensuring reliable operation of the gas turbine.

At the same time, the longitudinal dimensions are reduced, since it is not necessary to reconstruct the gas flow before feeding it to the heat exchanger, which reduces the length of the transition pipe between the gas turbine engine and the heat exchanger, and hence the gas turbine as a whole.

Claims (2)

1. The compensator of a gas turbine installation, comprising a thermoelastic corrugated shell installed between the inlet and outlet nozzles, an inner guide shell fixed at one end to the inlet pipe, and a shell located in its inner cavity forming the end portion of the diffuser of the gas turbine engine connected by ribs to the inlet pipe, the fact that the shell forming the end section of the diffuser is made in the form of a cone, a truncated apex of which is directed towards the gas lumen output. 2. The compensator according to claim 1, characterized in that its thermoelastic corrugated shell is made of two or more sections, and the sections are interconnected by bearing shells.