DE2300390A1 - GAS TURBINE ENGINE - Google Patents

Description

GAS TURBINE ENGINE The present invention is in the field of gas turbine construction, in particular gas turbine engines. Can be particularly advantageous the present invention in gas turbine aircraft engines for propulsion of missiles best limit are to be applied.

Gas turbine aircraft engines are known, e.g. after the British U.S. Patent No. 911 160, which includes a compressor and a combustor, which are connected to one another by means of an annular channel through which the ii compressors compressed air is supplied to the combustion chamber. With these engines a Part of the air behind the compressor for supplying iron icing systems, e.g. the inlet nozzle of the compressor of the gas turbine engine, the air intake of the Flugkbrpexs etc. as well as for operating the air conditioning in the pilot's cabin and taken from the passenger compartment. The gas turbine engine has to be connected to the Buftentnabse behind the compressor a receiver.

The shape of He is in two, opposite one of the air supplying the combustion chamber Channel executed symmetrically arranged annular spaces. These spaces are hollow Stand or hollow blades of the outlet nozzle of the final stage of the compressor in connection.

The annulus of the receiver, which is located above the combustion chamber Air-supplying channel is located, consists of the outer wall of the ring channel, the Outer casing of the combustion chamber and a diaphragm arranged on the side of the compressor.

The second, below the duct that supplies air to the combustion chamber located annular space of the receiver is through the inner wall of the ring channel, the inner housing the combustion chamber and the housing of the rear layers of the compressor rotor are limited.

For the entry of the air into the air supplying above the combustion chamber Receiver space located in the ring channel are in the outer wall of the mentioned channel Openings or a radial relative to the air flow entering the combustion chamber upward diffuser channel formed.

For the entry of the air into the air supplying below the combustion chamber Receiver space located in the ring channel are in the inner wall of the mentioned channel Openings or a radial air flow relative to the air flow entering the furnace downward diffuser channel formed.

However, there are cases of leakage with the gas turbine engines of seals of the bearings of the compressor rotor.

e Leakage of seals in the front bearing of the compressor rotor oil escapes from it into the air duct system of the Compressor. That Oil that has penetrated the air line system of the compressor is caused by centrifugal forces that affects it at the compressor outlet against the outer wall of the combustion chamber Print air supply ring duct.

Oil comes together through openings in the outer wall of the ring channel with air in the ring channel above the air supply to the combustion chamber Receiver room.

If the inner casing of the combustion chamber, which is below the receiver space located in the ring channel supplying air to the combustion chamber is limited, or in the event of a fault in the ab-bearing seals of the rear v of the compressor rotor oil gets directly into the receiver room.

The air in the receiver room has a high temperature because it is behind taken from the final stage of the compressor, in which during the compression process of the air at the same time as its pressure increase also an increase in its temperature takes place, which can be about 3000C and higher.

Under the influence of the high air temperature, the Pyrolysis of oil and the pyrolysis products, e.g. carbon oxide, get into the cabin and the passenger compartment of the missile and solve unpleasant sensations in the People (although they can even cause loss of consciousness).

There are known attempts to reduce the risk of oil penetration into the Air conditioning in the pilot's cabin and the passenger compartment as well as in the de-icing systems of the engine to belittle. For example, is a gas turbine engine (after British Patent No. 1 033 922) known which has a compressor, a combustion chamber and a duct connecting them and supplying air to the combustion chamber from the compressor having. A flow splitter is located in the duct that supplies air to the combustion chamber from the compressor arranged, which is attached to the front end of the flame tube of the combustion chamber. In the case of the mentioned power splitter, there is a receiver room for air extraction behind the Compressor formed. Air enters through openings in the front edge of the power splitter are carried out. The air extraction from the receiver is through Side openings are made in hollow stands that cover the outer and inner housings connect the combustion chamber bearing. The e.g. from the front v of the compressor in Oil that has penetrated the receiver settles inside the power splitter under the Influence of centrifugal forces.

Under the influence of a high air temperature inside the power distribution board However, the pyrolysis of the precipitated oil will take place0 The gaseous pyrolysis products together with the air, through rare openings in the stands mentioned, e.g. The air conditioning of the aircraft driver's cabin and the passenger compartment of the missile, which, as already stated, is very undesirable. In addition, there is a the risk that oil if the inner casing of the combustion chamber leaks on his Junction with hollow posts. which divert air from the bearing to the receiver, penetrates from the rear <of the compressor rotor into the systems mentioned.

Other attempts to reduce the risk of penetration are also known Oil in the receiver for air extraction behind the compressor of the gas turbine engine to diminish.

For example, a gas turbine engine is in accordance with the British patent No. 1 075 958 known1 that a compressor, a combustion chamber and a connecting them, the combustion chamber has air supplying duct from the compressor. At his front The end is the flame tube of the combustion chamber through hollow tubular stands on the outer housing attached to the combustion chamber.

For air extraction behind the compressor of this gas turbine form of The engine is provided with a receiver, which is divided into two, with respect to that of the combustion chamber The air supply duct is symmetrically arranged in a room. These rooms die together via hollow blades of the outlet nozzle of the final stage of the Compressor in connection.

The annulus of the receiver, which is located above the combustion chamber Air supply channel is located, consists of the outer wall of the channel, the outer housing the combustion chamber and a diaphragm arranged on the side of the compressor. The air inlet in this receiver space takes place via the above-mentioned hollow radial stand, which as fastening means of the front end of the flame tube on the outer casing of the combustion chamber serve and have an open removal end that is located on the inner wall of the combustion chamber Air supplying ring channel is arranged.

The second, below the duct that supplies air to the combustion chamber located annulus of the receiver is through the inner wall of the channel and the wall limited, which separates them from the rotor space of the engine. For air inlet in the mentioned receiver space are openings in the inner wall of the combustion chamber air feeding channel formed.

When oil penetrates into the air line system of the compressor or if the seals on the front bearing leak, it is caused by centrifugal forces thrown back against the outer wall of the duct supplying air to the combustion chamber and does not get into the receiver, which is used to extract air behind the compressor.

With the described gas turbine engine there is a risk of that oil penetrates into the receiver, e.g. in the case of a leaking bearing, the seal is damaged of the rear v of the compressor rotor and, if there is a leak, the underneath the the Brenikkammer air supplying channel located and to the rotor chamber of the engine adjoining receiver room.

As is apparent from the above, occurs in the known gas turbine engine the air extraction behind the compressor with complicated means that have considerable weight, which in total increases the weight of the missile brings with it.

The invention is based on the object of such a gas turbine engine to create, in which the receiver to the air vent behind the compressor constructively simple and easy and the risk of intrusion of oil in the de-icing system of the engine as well as in the de-icing and air conditioning systems the aircraft driver's cabin and the passenger compartment of the missile.

According to the invention, this object is achieved in that in the gas turbine plant, one compressor, one combustion chamber and one for air extraction behind the compressor serving receiver, whose space from the outer housing of the combustion chamber, the Outer wall of the duct supplying air to the combustion chamber and one on the side of the compressor arranged aperture is area, the receiver space on the part of the combustion chamber through the Aperture with openings for air entry into the receiver is limited, which with the one edge on the outer housing the ¼cct 3 inr and with the second edge on the outer wall of the duct supplying air to the combustion chamber is attached and arranged in such a way that that behind the receiver in the direction of the air flow between the panel and the Outer casing of the combustion chamber creates a dead water area.

The receiver for air extraction behind the compressor is in the form of a closed cavity formed which is not directly connected to the rotor chamber of the Engine borders. This leads to the oil being released when the seals leak, e.g. the rear bearing of the compressor rotor cannot get into the receiver.

To form the dead water behind the receiver in the direction of the air flow expediently has the aperture with openings, the receiver room limited by the combustion chamber, a conical section, the opposite the receiver space outer surface with the inner surface of the outer casing of the combustion chamber includes an acute angle. To carry out an even air withdrawal from the dead zone, it is advisable to use the openings to allow air to enter the receiver room to be carried out in the conical section of the diaphragm and to be arranged equidistantly on the circumference.

which is due to the uniform extraction of air from V dead water area the uniformity of the velocity field of the air flow in front of the combustion chamber not bothered.

If the seals, e.g. the front bearing of the Compressor RotoIz and when oil penetrates into its air / dead water pipe system it becomes far from the mentioned ç zone due to inertial forces in the direction of movement of the air flow thrown against the wall of the outer casing of the combustion chamber, whereby the possibility of oil penetration into the receiver space for air extraction behind the compressor is excluded. The out of 2 dead water area the receiver room The air supplied is fed into the de-icing and air-conditioning systems with the aid of extraction devices as well as in other systems of the engine and the missile.

The presence of only one receiver room for air extraction behind the compressor significantly simplifies the structure, reduces the overall weight the gas turbine engine and the missile.

Further features and advantages of the invention are referred to below an exemplary embodiment and associated drawings explained in more detail; show it 1 shows a schematic representation of the gas turbine engine according to the invention Longitudinal section, FIG. 2 a section along line II-II of FIG. 1, on an enlarged scale.

The two-circuit gas turbine engine, for example, has a compressor 1 (Fig. 1), a combustion chamber 2 and a compressor 1 with the combustion chamber 2 connecting and the latter supplying the compressed air in the compressor 1 Channel 3 on.

Part of the air behind the compressor 1 of the gas turbine engine is used to operate its de-icing system and the missile's de-icing system as well as the air conditioning of the pilot's cabin and the passenger compartment.

For air removal behind the compressor 1 is a receiver 4, whose Space 5 through the outer casing 6 of the combustion chamber;, the outer wall 7 of the of the compressor 1 of the combustion chamber 2 air-supplying duct 3, one of which is grounded on the part of the compressor 1 Diaphragm 8 and a diaphragm 9 arranged on the side of the combustion chamber 2 with openings 10 (Fig. 2) for air entry into the space 5 (Fig. 1) of the receiver 4 is formed. The outer wall 7 of the duct supplying air from the compressor 1 to the Breilnkaamer 2 3 consists of the kiss ring 11 of the outlet guide apparatus 12 of Compress 1 and the outer wall 13 of the diffuser of the combustion chamber 2.

The panel 9 with openings 10 (Fig. 2) for air entry into the room 5 (Fig. 1) of the receiver 4 is with one edge on the outer housing 6 of the combustion chamber 2 and with the other edge on the outer wall 7 of the air supplying the combustion chamber 2 Channel 3 attached and arranged in such a way that between it and the (dead water area) Outer housing 6 of the combustion chamber 2 creates a dead zone 14.

To ensure the formation of the dead zone 14 is the one with openings 10 provided (Fig. 2) Aperture 9, the space 5 of the receiver 4 for air removal behind the compressor 1 on the part of the combustion chamber 2 (Fig. 1) limited, with a conical Section 15 executed. The outer surface of the conical section 15 of the diaphragm 9 closes with the inner surface of the outer housing 6 of the combustion chamber 2 a pointed Angle, which increases the cross-sectional area for the air flow at the inlet the combustion chamber 2 suddenly increases, i.e. a so-called diffuser is created with sudden expansion.

The openings 10 (Fig. 2) for air entry into the room 5 (Fig. 1) of the receiver 4 for air extraction behind the compressor 1 are in the conical section 15 of the diaphragm 9; e forms and is arranged equidistantly on the circumference.

The gas turbine engine operates as follows.

The air sucked in by the gas turbine engine from the environment is compressed in its compressor 1 and ½r.or lXe Channel 3 of the Combustion chamber 2 supplied. The one between the combustion chamber 2 and the outlet duct 12 of the compressor 1 located portion of the channel 3 forms the diffuser of the Combustion chamber 2. When the air flow supplied by the compressor 1 moves over the section of the channel 3, which represents the diffuser of the pulp chamber 2, takes its speed from The flow is at the edge 16 of the outer wall 13 of the Tear off the diffuser of the combustion chamber 2, creating an air vortex in the dead zone 14 forms, from which the air flows through the in the conical section 15 (Fig. 1) of the Aperture 9 executed openings 10 (FIG. 2) sucked into the space 5 of the receiver 4 will.

Bearings If there is oil from the front v of the compressor 1 into the If air flow enters, it will because of the inertial forces as it exits the diffuser at the edge 16 no sudden reversal in the direction of flow at a greater distance., Learn steering, but only v from the dead zone 14 against the wall of the outer housing 6 of the combustion chamber 2 is not thrown and can thus “get into the receiver 4”.

The air supplied from the dead zone 14 to the room 5 of the receiver 4 is made by several openings 17 formed in the outer housing 6 of the combustion chamber 2 (Fig. 2) and through stand 18 with flanges 19 in the de-icing systems of the engine and the missile and in the air conditioning systems of the cabin and the passenger compartment (not shown) as well as in other systems of the engine and the missile taken. The stands 18 are between the outer housing 6 of the combustion chamber 2 and one Housing 20, -that the second circuit of the gas turbine engine surrounds, the openings 17 arranged opposite.

Claims (3)

PATENT CLAIMS S gas turbine engine, which has a compressor, a combustion chamber and has a receiver serving for buft extraction behind the compressor, whose Space from the outer casing of the combustion chamber, the outer wall of the combustion chamber air feeding channel and an aperture arranged on the side of the compressor is that it is not shown that the room (5) of the receiver (4) on the part of the combustion chamber (2) through a screen (9) with openings (10) for air inlet in the space (5) of the receiver (4), the one with one edge on the outer housing (6) of the combustion chamber (2) and with the other edge on the outer wall (7) of the combustion chamber (2) Air supply duct (3) attached and arranged so that behind the receiver (4) in the direction of the air flow between the panel and the outer housing (6) the combustion chamber (2) creates a dead water area. 2. Gas turbine engine according to claim 1, d a d u r c h g e k e n It should be noted that the diaphragm (9) with openings (10) has a conical section (15) has, the opposite of the space (5) of the receiver (4) outer surface with the inner surface of the outer housing (6) of the combustion chamber (2) an acute angle includes. 3. Gas turbine engine according to claim 2, d a d u r c h g e k e n It is not indicated that the openings (10) to the air entry into the space (5) receiver (4) is formed in the conical section (15) of the diaphragm (9) and are arranged equidistantly on the circumference.