JPH03249301A - Reactive jet turbine - Google Patents

Abstract

PURPOSE: To improve the turbine efficiency and the reliability during operation in a low-temperature fluid by forming the outlet parts of supply pipes into the form of a feed nozzle, the least cross-sectional area of which is smaller than that of a thrust nozzle. CONSTITUTION: In a rotor 1, the end part-inlets 5, 6 of axial passages 3, 4 of a shaft 2 face each other across clearances δ. In this case, the least cross-sectional areas of feed nozzles 19, 20 of the supply pipes 17, 18 are formed smaller than those of thrust nozzles 12, 13 of jet pipes 10, 11. Thus, it is certain that impulse waves are generated at the end part-inlets 5, 6, and since the leak of fluid from the clearances δ becomes almost zero, the turbine efficiency is improved, and the reliability during operation in low-temperature fluid is also improved.

Description

DETAILED DESCRIPTION OF THE INVENTION Field of the Invention This invention relates to turbine manufacturing, and more particularly to reaction jet turbines.

The present invention is most advantageously used in output actuators for a variety of systems, particularly reversible actuators for shutoff and control couplings.

[Conventional technology]

Known in the art are various types of air and gas blade turbines: axial flow, radial flow and cross flow turbines (N, N.

Bykov et al., “Parameter Selection and Design of Low Power Turbines for Starting Mechanical Units,” I Masinos
Troenie Publishing House, Moscow, 1972 p31,
(See Figure 2.1; p196, Figure 7.8; p199, Figure 7.9). These turbines include a rotor formed in the form of a shaft journaled in bearings and at least one runner with blades. A supply device is provided in the casing for supplying fluid (liquid or gas) to the runner. This feeding device may be in the form of a fixed set of blades or in the form of a feeding nozzle. Downstream of the runner and in the direction of fluid flow, a discharge device is provided which includes a diffuser (bladed or non-bladed).

Prior art turbines convert the potential energy of a fluid into mechanical work at a rotor shaft by changing the flow direction and expanding the fluid. This ensures that the turbine has sufficiently high power parameters, at least comparable to those of other engines. However, these turbines are characterized by high effort and precision requirements caused by the intricate three-dimensional geometry of the rotor and fixed blades (small gaps between the rotor and fixed blades, fixed blades or nozzles and It is difficult to manufacture due to the accuracy of the relative position of the rotor plates. Moreover, the construction of turbines based on the prior art requires that they be in the form of multistage units to ensure high efficiency (in case of high pressures of the available fluid (i.e. high enthalpy differences)) Extremely complex. When operating with wet and/or contaminated fluids, the reliability and service life of the turbine may be affected due to corrosive wear or contamination of the blades, and also due to ice at sub-zero temperatures of the fluid. Decreased due to blockage of the inter-blade passages and ice formation on the blades.

The relatively high moment of inertia of the rotor, especially in multi-stage turbines, impairs the dynamic properties and as a result requires sophisticated control systems, and for this reason such turbines are often used as actuators in the overall system. cannot be used. Furthermore, the need to provide for such turbine reversals makes the structure much more complex.

A rotor having at least one axial passage in its shaft (which shaft has a thrust nozzle at its distal end communicating with the inlet of the axial passage to form a continuous gas duct) is known in the art. Reaction jet turbines are known (V , V
, 5 olodovnikov et al. [Technology Cyhanetics, Design and Components of Automatic Control Systems, Vol. 3]
Vol., Actuators and Servo Mechanisms.

Mashinostroenie Publishing House, Moscow, 1
976, p519.520. Figure X I, 8;
p 539-543. Figure X1.17N, 1. Kiri
“Turbomachine Theory” by Lov et al. High school textbook, Mas
h 1nos troen ie publisher, Leningrad, 1974, 287-90, Figure IV-4HD, L
, 5hirer [Pneumatic Components for Extremely High Temperatures and Severe Radiation], Proceedings of the 2nd World Congress of the International Federation of Automatic Control Equipment, Hasel, Switzerland, Automation Equipment Volume 19
1965, Nauka Publishing House, Moscow, p. 54-57).

Reaction jet turbines based on the prior art utilize available energy in the form of fluid pressure (available enthalpy) with the generation of a reaction thrust at the thrust nozzle and the generation of torque on the rotor shaft developed by the thrust, respectively. A plateless turbine in which the torque (mechanical work) on the shaft is developed by direct conversion of the jet escaping from the thrust nozzle into kinetic energy. Compared to bladed turbines, reaction jet turbines according to the prior art have a number of advantages, such as the simple structure of the rotor and therefore the low manufacturing effort due to the absence of complex blade sets and precise gaps. The available high fluid pressures can be used in a single stage as the flow moves through the gas duct and expands in the nozzle under conditions very close to isentropic conditions, thereby achieving ultra-high velocities at the exit of the nozzle; Efficiency increases with increasing pressure. Expansion efficiency (adiabatic expansion efficiency or polytropic efficiency) is primarily determined by the nozzle velocity coefficient.

η−, −ψ2 h.

In the formula, h is the effective specific work of expansion (specific enthalpy)
And h1! '' is the specific work (specific enthalpy) corresponding to an isentropic process, is the actual escape velocity from the nozzle, and C5 is the escape velocity corresponding to an isentropic process).

Since the flow occurs in the nozzle without interruption and without shock waves, the velocity coefficient reaches ψ”!0.99 for shaped nozzles and ψ”0.97-0.98 for unshaped conical nozzles.
Therefore, the expansion efficiency is sufficiently high. The power efficiency of a reaction jet turbine according to the prior art is also determined by the square of the effective escape velocity (specific impulse of the nozzle) or the specific thrust of the nozzle, P, which is the ratio of the thrust P (in kgf) to the flow G (in kg/s). It can also be expressed in the form of the nozzle thrust efficiency, which is directly proportional to the square of (that is, T=). The specific parameters of the nozzle mentioned above increase with increasing fluid pressure upstream of the nozzle, thus making it possible to obtain a high power efficiency of reaction jet turbines based on the prior art at high fluid pressures due to the expansion in a single stage. . Furthermore, in such a turbine, the fluid flow velocity in the gas duct upstream of the nozzle is low and the water pressure loss in the duct is kept to a minimum, so there is no need for any special shaping of the gas duct passage. The efficiency of a reaction jet turbine is similarly
It can also be enhanced by using the compressor effect that occurs in the rotor jet pipe during rotation.

Turbines according to the prior art are characterized by an almost complete absence of failures due to ice formation in the gas duct passages during operation with cold and humid gases.

This is due to the fact that there is no dead zone, and also a large drop in gas temperature and moisture precipitation at the point of expansion, since there is almost no boundary layer within the minimum (critical) cross-section of the nozzle. This is explained by the fact that moisture droplets only occur within the nozzle where they are blown away from the nozzle wall by the high velocity gas flow. Furthermore, another feature of this turbine is the relatively low intensity of corrosive wear of its components due to the absence of elements (blades) that are directly attacked by corrosive particles. At the same time, efficiency is reduced due to the aerodynamic drag of the jet vibe in the environment, along with high ambient rotor speeds.

In addition, working with humid contaminated gases with high ambient velocities
The complexity of the construction of the friction elements of the feed device with moving contact seals limits the field of application of such turbines. The field of application of these turbines according to the prior art is also limited by the use of non-contact seals. This is because the sealing members become clogged with dirt, wear, or freeze during operation with humid, contaminated, and cold gases.

The use of non-contact seals also results in reduced efficiency due to fluid leakage therethrough.

The art also describes a rotor in the form of a shaft having at least one axial passage and a thrust nozzle at its distal end communicating with an end outlet of the axial passage to form a continuous gas duct. On the other hand, reaction jet turbines are also known which include at least one jet vibrator cantilevered against the shaft and a supply tube positioned coaxially with the shaft and spaced apart from its end (E, V, Gertz, “Pneumatic and Hydraulic Actuators and Control Systems J, No.
, 10゜1984; V. V. 5ayapin “
"Optimization of Parameters of Pneumatic Actuators with Impulse Motors" Mashinostroenie Publishing House, Moscow, p. 58, see Figure 1).

The fluid (gas) supply in this reaction jet turbine is passed through a gap into the end inlet of the axial passage of the shaft to simplify the design and increase reliability in operation with humid, contaminated, and cold fluids. This is done in the form of a jet from the incoming supply pipe.

However, efficiency is reduced as a result of leakage of fluid through the space between the end inlet of the axial passage of the shaft and the supply tube.

[Problem to be solved by the invention]

The present invention provides a reaction jet turbine having a feed tube constructed to substantially eliminate fluid leakage, thereby increasing the efficiency of the turbine and increasing its reliability during operation with humid, contaminated, and cold fluids. It is based on the challenge of providing

[Means for solving the problem] This problem consists of a rotor in the form of a shaft having at least one axial passage, a thrust nozzle thereof communicating with the end inlet of the axial passage to form a continuous gas duct. at least one jet pipe having a distal end and cantilevered relative to the shaft; and a supply pipe in the form of a feed pipe positioned coaxially with the shaft and spaced apart from the end thereof. According to the invention, the outlet section of the feed pipe is made in the form of a feed nozzle with a minimum cross-sectional area smaller than the minimum cross-sectional area of the thrust nozzle; The ratio of these areas is solved by a reaction jet turbine, which is characterized by ensuring a shock wave in the inlet zone of the axial passage of the shaft.

By equipping the supply pipe outlet section in the form of a supply nozzle, weak perturbations (flow of gas from the axial passage under the action of differential pressure) cannot propagate against the supersonic flow and (pressure (waves propagate at the speed of sound), which almost completely eliminates fluid leakage from the axial passages of the shaft through the interstitial space, as very little leakage can occur along the thin boundary layer, which has a velocity below the speed of sound. It is possible to accelerate the fluid with supercritical pressure ratios in the filter and feed it into the axial passage of the shaft at supersonic speeds.

The fact that the minimum cross-sectional area of the supply nozzle is smaller than the minimum cross-sectional area of the thrust nozzle is a necessary condition for supersonic supply of fluid to the axial passage of the shaft according to the following theoretical relationship: where: where S3 is the minimum cross-sectional area of the feed nozzle, S is the minimum cross-sectional area of the thrust nozzle, and σ is the total pressure recovery coefficient (energy recovery, where Po is the total pressure upstream of the thrust nozzle,
pH 3 is the total pressure upstream of the feed nozzle.

By equipping the feed and thrust nozzles with a minimum cross-sectional area in such a proportion as to ensure a shock wave (transition from supersonic to subsonic fluid flow) in the inlet zone of the axial passage of the shaft, engineering Losses are kept to a minimum (total pressure recovery coefficient σ tends to its maximum value).

This is because fluid flow through the axial passage at supersonic speed upstream of the shock wave would otherwise involve higher energy losses if the shock wave is far from the inlet. On the other hand, if the shock wave is outside the axial passage, within the interstitial space and at a certain distance from the end inlet, a large amount of fluid will flow from the axial passage of the shaft into the interstitial space between this shock wave and the end inlet. leakage occurs. Most preferably, the above-mentioned nozzle can be fabricated with a theoretical ratio = σ3 (k being the experimental coefficient) corresponding to the value of S3 obtained when the shock wave is directly in the cross-section of the end population. be. In this case, the reduction in the specific thrust caused by a small leakage of fluid to the extent of acidification is largely compensated by the increase in the specific thrust due to the reduction in losses in shock waves of lower strength. This is because the supersonic jet does not expand in the interstitial space to the size of the cross-sectional area of the end inlet of the axial passage of the shaft, and the velocity of the jet upstream of the shock wave in this interstitial space is This is because the velocity is lower than the velocity upstream of the shock wave within the cross section of the population.

By providing the outlet part of the supply pipe in the form of a supply nozzle, it is possible to increase the space between the end inlet of the axial passage of the shaft and the supply nozzle compared to the case of the prior art, and thus the invention fewer requirements are placed on the fabrication of reaction jet turbines based on contact between the end of the shaft and the end face of the feed nozzle and moisture droplets can flow freely through the interstitial space at the point of shutdown of the reaction jet turbine. Their authenticity will be enhanced by completely preventing their freezing of each other due to the possibility of escape.

The supply nozzle is preferably made in the form of a supersonic nozzle.

If the supply nozzle is a supersonic nozzle, for example, a lahar nozzle (L
aval nozzle), the acceleration of the fluid flow to supersonic speed takes place upstream of the end inlet of the axial passage of the shaft. At the same time, if a tapered sonic nozzle is used, shock waves may appear prematurely in the interstitial space under conditions of (low supercritical pressure ratio in the feed nozzle), leading to significant fluid leakage. It causes

In order to ensure that the jet enters the axial passage of the shaft over its entire cross section and thus eliminates direct leakage from the jet, the amount of space between the end face of the supply nozzle and the end of the shaft is It is preferably selected based on the following formula: 2tgγ/2 where δ is the amount of space between the end face of the feed nozzle and the end of the shaft, and D is the diameter of the axial passage of the shaft. , D is the diameter of the end face of the supply nozzle, and γ is the taper angle of the outlet portion of the supply nozzle.

〔Example〕

The reaction jet turbine according to the invention comprises a rotor 1 (FIG. 1) in the form of a shaft 2 with two mutually insulated axial passages 3, 4. Both ends of the shaft 2 are provided with end inlets 5.6 of respective axial passages 3.4. The shaft 2 is journaled in a bearing 7 (for example in a rolling or sliding contact bearing) and has a drive gear 8 for transmitting torque to an actuator (not shown).

A bushing 9 placed on the shaft 2 supports two cantilevered radially extending end pipes 10, 11 each having a thrust nozzle 12, 13 at its distal end. The thrust nozzles 12 , 13 are laterally single and co-oriented in relation to the joint axis of the shaft 2 in order to develop a torque on the shaft 2 under the action of a thrust.

The thrust nozzles 12, 13 communicate with the respective axial passage 3.4 and its end ports 5, 6 through the interior space of the jet pipe 10.11, respectively, to form a continuous gas duct.

Jet pipe 10.1 to reduce fluid pressure losses
1 (Fig. 2) are made curved and each jet pipe 10.11 has a fairing ( Fairing) 16 (Figure 2). Furthermore, to reduce aerodynamic drag, the jet pipes 10.11 can also be made without fairings, but in this case they have a streamlined cross-section, i.e. an elliptical shape as shown in Figure 3. Must have. When the end pipe has a ring-shaped cross section, the fairing 16 has a streamlined cross section, for example, an elliptical cross section as shown in FIG.

To achieve this, it has a curved cross-sectional shape to be constructed with a doped pipe 10.11.

In order to quickly replace the thrust nozzles 12, 13 (FIG. 5) when they wear out rapidly, or if it is necessary to recalibrate the reaction jet turbine for different parameters, the thrust nozzles 12, 13, respectively It may be in the form of a ready-to-remove bushing mounted in a special socket bored into the distal end of the jet pipe 10,11.

End inlet 5.6 coaxially with axial passage 3.4 (Fig. 1)
A pair of gas dynamic supply devices in the form of supply pipes 17 and 18 are provided upstream of the pump.

The outlet portions of the supply pipes 17 and 18 are respectively supply nozzles 1
It has a 9°20 shape. The supply nozzles 19, 20 in this example are in the form of supersonic Laval nozzles.

End faces 21 and 22 of supply nozzles 19 and 20, respectively (
A space δ is constructed between the end population 5.6 (Fig. 6) and the end population 5.6. The amount of space δ is selected based on the following formula: where D is the diameter of the axial passage 3 (4) of the shaft 2 and D2 is the end face 21 (
22), T is the taper angle of the outlet section of the supply nozzle 19 (20).

A reaction jet turbine works as follows.

In order to rotate the rotor 1 (Figure 1) clockwise (when viewed from the distal end of the rotor 1, i.e. on the left side of the figure), the fluid (
gas produced by a gas generator, air or compressed gas)
is fed under pressure to the feed line 17 of the gas dynamic feed device, where it is accelerated to sonic or supersonic speeds in the sonic or supersonic feed nozzle 19, respectively (this is due to the supercritical pressure in the feed nozzle). ). A steady supersonic jet is formed downstream of the end face 21 of the feed nozzle 19 (FIG. 6) in the axial space δ with a rigid (impermeable) boundary around it. This supersonic engine travels through the axial space δ and enters the axial passage 3 of the shaft 2 through the end inlet 5. The jet is in the axial passage 3
Gas dynamic sealing of the axial passage 3 by supersonic flow occurs if the jet boundary contacts the internal surface of the axial passage or around the cross-section of the end inlet 5. . This sealing is based on the fact that weak perturbations (shock waves) propagate at the speed of sound and cannot pass against supersonic flow. Owing to the presence of the pressure difference, leakage of fluid from the axial passage 3 into the space δ is therefore largely prevented. In order to ensure a supersonic velocity in the inflow of the fluid into the axial passage 3 and to enable the greatest possible increase in the spatial δ-view, the shape of the supersonic jet is adapted to the conditions of escape from the supply nozzle with underexpansion. (in FIG. 6 the boundaries of the jet are shown in the form of two curves), i.e. the pressure at the end face 21 of the supply nozzle 19 must be greater than the surrounding pressure, or else there is a design deviation. (in FIG. 6 the boundary of the jet is shown in the form of a dotted line), i.e. the pressure at the end face 21 of the supply nozzle 19 is equal to or approximately equal to the ambient pressure. Must be equal. The necessary conditions for the escape of the jet from the supply nozzle 19 are: (the ratio of the area of the end face 21 to the minimum cross-sectional area). The conditions for the inflow of the jet into the end inlet 5 over its entire cross-section rather than over a part of it, and thus the exclusion of leakage from the peripheral parts of the jet,
It is determined by the ultimate allowable increase in space volume δ11X. That is, the space quantity δ must satisfy the following inequality: Note that this was derived by taking into account the geometry of the supersonic jet. After the inflow of the supersonic jet through the end inlet 5, a feed nozzle 19 and a thrust nozzle 12 (FIG. 5) compatible with the conditions necessary for the inflow of the supersonic jet into the axial passage 3 (FIG. 6). According to the minimum (critical) cross-sectional area ratio of
(Fig. 6) directly or at a certain distance from the end inlet 5 in the axial passage 3 at a distance of <δ3;
A shock wave appears in the axial passage 3 of the shaft 2:'S
IJ In the formula, 33 is the minimum (critical) cross-sectional area of the supply nozzle 19, S is the minimum (critical) cross-sectional area of the thrust nozzle 12 (Fig. 5), and D3 is the minimum (critical) cross-section of the supply nozzle 19 (Fig. 6).
critical) cross-sectional diameter, D is the thrust nozzle 12 (Fig. 5)
The diameter of the smallest (critical) cross section of , σ is the total pressure recovery coefficient.

The subsonic to supersonic velocity transition of the fluid stream occurs within the shock wave. In the sixth installment, shock waves are shown in the form of vertical wave lines, where the flow conditions are characterized by velocity coefficients. This velocity coefficient λ is the ratio of the velocity of the flow at a given point to the velocity of sound at the critical cross section.

The working efficiency of the reaction jet turbine is determined by the supply nozzle 19 (
The thrust nozzle 12 (FIG. 5) is characterized by the value of the ratio of the thrust nozzle 12 (FIG. 5) whose cross section (FIG. 6) is the minimum one with a constant area (the ratio thrust) to the area S (FIG. 7) (FIG. 7). In the diagram shown in Figure 7, (・)
1 corresponds to the condition of −S=σ3 and the position of the shock wave within the cross section of the direct end population 5 (λ, 〉1; λ+z<1)
. In the diagram (FIG. 7), (.)2 corresponds to the blockage (reduction) of the area of the thrust nozzle 12 (FIG. 5), and represents the relationship of σ3 to S=. Note that the formula includes an empirical coefficient (k=1-2). This (·)2 corresponds to the maximum value of the specific thrust at which the shock wave (Fig. 6) lies at a short distance from the upstream end inlet 5 in the direction of flow, i.e. directly within the space δ (D = D). , )(λz+>1
;λ2□<1 and λ21<λ1. ). At this position of the shock wave, a certain amount of leakage of fluid into the space between the shock wave and the end inlet 5 occurs, but due to the decrease in the strength of the shock wave it reaches its maximum value under the specific thrust. That is, P−P□ (λ2I<λ11). When the thrust nozzle (12) (5th time) is further blocked, the spacing of the shock waves becomes larger, resulting in a strong increase in fluid leakage and a decrease in the specific thrust, respectively (zone A in Fig. 7). ).

When the area of the thrust nozzle 12 (Fig. 5) is "opened" (increased) to a value much larger than that at the theoretical point (·) 1 (Fig. 7), as indicated by (·) 3, The shock wave will move in the flow direction to a position inside the axial passage (3) (Fig. 6) (λ31
>λ, 1 and λ3. 〉■, λzz<1). As a result, even though the strength of the shock wave is reduced, the specific thrust l' is reduced due to the energy loss during the movement of the supersonic flow through the axial passage 3 (Fig. 6) upstream of the shock wave. occurs (zone B) (λ3I<λI+). Therefore, (・)2(
The area ratio of the minimum cross section of the supply nozzle 19 and the thrust nozzle 12 (FIG. 5), which corresponds to the area value of FIG. represents the position of the shock wave within.

The fluid flow flows through the axial passage 3 and the interior 1 of the jet vibrator 10.
4 (FIG. 1) to the thrust nozzle 12. The fluid stream is again accelerated within the thrust nozzle 12 and expelled into the environment.

In other words, the potential energy of the fluid is
With the development of the reactionary thrust at , it is converted into kinetic energy of the jet.

The thrust -P- in the thrust nozzle 12 develops a torque on the shaft that is oriented clockwise thanks to the arm of the jet vibe 10. This torque is
It is transmitted to the actuator via the drive gear (8). The rotor rotates in bearings and mechanical work is performed.

To transmit torque in the opposite direction (counterclockwise) to the actuator (ie for reversal), fluid is supplied to the opposite supply device or supply pipe 18. Note that at this time, the fluid supply to the supply pipe 17 is interrupted. The fluid flow similarly moves in accordance with the cycle described above, with the fluid entering the end inlet 6 of the axial passage 4 of the shaft 2 after the supply nozzle 20 and then passing through the interior of the jet vibrator 11 to the thrust nozzle 13. It moves up to the point where it is accelerated, and is pushed out to develop a recoil thrust. The recoil thrust at the nozzle 13 develops a torque with the arm of the jet vibrator 11 at the shaft 2 oriented counterclockwise. This torque is transmitted to the actuator by the drive gear 8.

In the case of reaction jet turbines where precise control is required (e.g. servo control systems), the fluid is distributed under differential pressure in both supply pipes 17 upstream of the supply pipes according to the controlled value error and its preset value. 18 may be supplied simultaneously.

The reaction jet turbine according to the invention is widely used in gas engines in joint drive mechanisms of combination gas control devices, such as the actuators of a series of ball valves with a nominal internal diameter of 300 to 1400 mm for a nominal pressure of 8 MPa. Can be used. FIG. 8 shows an engine with a casing 23 housing a reaction jet turbine according to the invention.

The supply device 17 of the turbine is mounted on the end plate 24 of the casing 23, and the supply device 18 is mounted on the end plate 25. The bearing 7 of the turbine shaft 2 is mounted on a partition 26 which divides the interior of the flange casing 23 into two compartments, compartment 27 and compartment 28 . Compartments 27 house jet vibrators to, ii with thrust nozzles 12, 13, respectively. Compartment 28 houses a reduction gear 29 having an output shaft 30 and countershafts 31,32. Shirt of the speed reducer 29 in the form of sealed bearings) 30, 31
, and 32 are mounted on the partition wall 26 and on the end plate 25 which is the end plate of the speed reduction device 29. The same end plate 25 supports the second feed device 18 and the second bearing 7 of the shaft 2. The partition wall 26 sealingly separates the spaces 27 and 28 so that discharged fluid cannot enter into the deceleration device 29.

The drive gear of the reduction gear 29 is the drive gear 8 of the shaft of the reaction jet turbine. gear 8
is located between shaft 20 bearing 70 and within compartment 28 . A discharge chamber 33 is mounted on top of the casing 23 and the interior 3 of this chamber
4 into compartment 2 through port 35 in bulkhead 26.
I am in contact with 7.

This engine has a steering wheel 37 which, if required, connects the steering wheel to the output shaft 30 of the reduction gear 29 (for manual operation) and automatically disconnects them when pressure is supplied to the reaction jet turbine. It has a manual mechanical actuator in the form of an interlock device.

This engine works as follows.

When gas is supplied to the turbine through one of the supply devices 17, 18, the turbine shaft 2 rotates in the respective direction. Torque from the shaft 2 is transmitted through the drive gear 8 and the reduction gear 29 to the output shaft 30 of the reduction gear and then to a successor actuator or cranked by a "screw-and-nut" drive mechanism (not shown). transmitted through a mechanism. In the absence of any fluid pressure, the actuator of the coupling can be operated manually by means of a hand wheel 37 which is securely connected to the output shaft of the reduction gear 29 by an interlock device 36. To ensure safety in case fluid is inadvertently supplied to the reaction jet turbine, the device 36 automatically disengages the handle wheel 37 from the output shaft 30 at the point of pressure application. During operation of the reaction jet turbine, the thrust nozzles 12, 13
The evacuation fluid expelled from the diaphragm 26 is drawn into the interior space 34 of the evacuation chamber 33 through the port 35 of the septum 26 and then discharged to the outside or removed into a collection manifold (not shown).

〔Effect of the invention〕

The reaction jet turbine based on the present invention can be effectively and widely used in various technical fields. It has potentially high power parameters compared to other types of turbines, and it is a thermodynamic process that is close to isentropic, converting fluid energy into kinetic energy in a recoil jet and then into mechanical work in a single stage. This is because it is directly converted by . The efficiency of the turbine according to the invention increases as the pressure of the available fluid increases, with the initial temperature of the fluid varying from -60°C or even lower sub-zero temperatures to high temperatures ranging from 1000 to 1500°C and above. I can do it. The structural simplicity of the turbine is due to its design, which is single stage for all fluid pressures, and the simplicity of the flow duct without the need for shaping also results in a low moment of inertia of the rotor, i.e. a high dynamic properties, its light weight and overall small size, and its high reliability when operating in contaminated, humid and cold fluids. This reliability is also due to the use of the original non-contact gas dynamic feed system. These advantages make it suitable for use as output components in actuators of various systems and units with outputs ranging from a few watts to megawatts, in control systems including, for example, servo systems, and in couplings for gas control equipment operating with contaminated, humid, and cold gases. This provides for effective use of the reaction shet turbine in accordance with the present invention in actuators of aircraft, in drive mechanisms of turbopump and turbocompressor plants, in gas turbine engines of aircraft, and the like.

[Brief explanation of drawings]

FIG. 1 is a longitudinal sectional view of a reaction jet turbine according to the present invention, FIG. 2 is an axial view of the reaction jet turbine shown in FIG. 1, and FIG. 4 is a sectional view taken along line IV-IV in FIG. 2, and FIG. 5 is an enlarged longitudinal sectional view of one embodiment of the thrust nozzle. , Figure 6 is
An enlarged view cut along the arrow ■ showing a schematic diagram of the fluid flow,
FIG. 7 shows the relationship of the specific thrust to the minimum (critical) cross-sectional area of the thrust nozzle when the minimum (critical) cross-sectional area of the supply nozzle is constant; FIG. 8 shows the reaction jet according to the invention; 1 is a longitudinal sectional view of an engine of a joint combination drive mechanism of a gas control device using a turbine. 1...Rotor, 2...Shaft, 3.
4... Axial passage, 5, 6... End population, 7...
・Bearing, 8... Drive gear, 9...
・Bush, 10, 11... Jet pipe, 12, 13... Thrust nozzle, 14, 15... Internal space, 16... Fairing, 17, 18... Supply pipe, 19, 20
... Supply nozzle, 21, 22... Supply nozzle end face. /'15 J Fda4 FEgaf/li 7

Claims (1)

Claims: 1. A rotor in the form of a shaft (2) having at least one axial passage (3), an axial passage mounted on the shaft and at its distal end forming a continuous gas duct. at least one jet pipe (10) having a thrust nozzle (12) in communication with the end inlet (5) of (3) and coaxial with the shaft (2) and spaced apart from its end; (δ) In a reaction jet turbine comprising at least one gas dynamic supply device in the form of a supply pipe (17) positioned in a reversed state, the outlet part of the supply pipe (17) is connected to the thrust nozzle (12). in the form of a feed nozzle with a minimum cross-sectional area (S_3) smaller than the minimum cross-sectional area (S) of A reaction jet turbine characterized by ensuring a shock wave of. 2. Reaction jet turbine according to claim 1, characterized in that the feed nozzle (19) is a supersonic nozzle. 3. The end face (21) of the supply nozzle (19) and the shaft (2
The amount of space (δ) between the ends of D_1: diameter of the axial passage of the shaft; D_2: diameter of the end face of the supply nozzle; r: taper angle of the outlet portion of the supply nozzle. A reaction jet turbine according to clause 1.