CN115355108B

CN115355108B - Rotary gas generator without turbine shaft power output

Info

Publication number: CN115355108B
Application number: CN202210759254.6A
Authority: CN
Inventors: 崔涛; 尚伟; 郑耀; 黄日鑫
Original assignee: Zhejiang Institute Of Turbomachinery And Propulsion System
Current assignee: Zhejiang Institute Of Turbomachinery And Propulsion System
Priority date: 2022-06-29
Filing date: 2022-06-29
Publication date: 2024-09-13
Anticipated expiration: 2042-06-29
Also published as: CN115355108A

Abstract

The invention discloses a rotary gas generator without turbine shaft work output, which removes a turbine pump, a combustion chamber and a nozzle of a traditional liquid fuel engine, combines the rotary gas generator into a structure, takes a self-contained propellant as a working medium, and enables the propellant to pass through an oil delivery shaft before entering the rotary gas generator, the oil delivery shaft is arranged on the engine shaft line and synchronously rotates with the engine, the propellant can be self-ignited after contacting and collision, and the gas generator and the shaft work output integration under the condition without the turbine structure can be realized without an additional ignition system.

Description

Rotary gas generator without turbine shaft power output

Technical Field

The invention relates to the field of aviation aerospace propulsion, in particular to a rotary gas generator without turbine shaft power output.

Background

In recent years, with the progress and development of science and technology military, the field of aerospace propulsion technology gradually draws attention of various countries due to the potential military and civil value of the aerospace propulsion technology, and various countries in the world have conducted a series of researches on aerospace propulsion systems. The research of thermodynamic cycle, in particular novel thermodynamic cycle and corresponding novel thermodynamic process is a permanent research direction in the technical field of aerospace propulsion, and new cycle and combined cycle are continuously explored in the future, so that the thermal efficiency is greatly improved by support.

The existing aerospace propulsion system comprises various aeroengines, rocket engines, ramjet engines and piston engines, and has respective performance advantages and ideal flight airspace. The rocket engine is not limited by the conditions of height and initial speed, but has lower performance and high propellant consumption rate; aeroengines are characterized by high performance but are limited by the temperature endurance limit of the turbine. The temperature limit of the turbine is always a core constraint factor for improving the thermodynamic cycle efficiency of the engine, and the influence of the temperature limit of the turbine on the thermodynamic cycle efficiency is more critical with the increase of the incoming flow temperature under high-speed flight, and even becomes a key for determining whether a thermodynamic cycle mode is feasible. In order to improve the upper limit of the flying speed of the turbine engine, the gas generator is introduced to generate gas to replace high Wen Lailiu air, so that the air turbine rocket combined cycle engine is a feasible scheme facing high-speed flying. Yet another significant problem with this engine is that it is difficult to compromise the overall performance at high and low speeds, where turbine temperature extremes remain critical factors limiting the operating temperature of the gasifier and thus the efficiency of the engine's thermodynamic cycle.

Disclosure of Invention

Aiming at the defects of the prior art, the invention provides a rotary gas generator without turbine shaft power output, which has the following specific technical scheme:

The rotary gas generator comprises a lateral fuel oil sealing cavity, a lateral oxidant sealing cavity, a front bearing seat, a bearing sleeve, a combustion chamber body and a spray pipe;

The combustion chamber body 5 comprises a main shaft 501 which extends out and a combustion chamber cavity 508 which is internally arranged; the main shaft is a stepped concentric shaft sleeve shaft and comprises an inner solid section, a middle thin-wall section and an outer thin-wall section which are sleeved together; a fuel flow passage I is formed in the middle-layer thin-wall section, an oxidant flow passage I is formed in the outer-layer thin-wall section, and the fuel flow passage I and the oxidant flow passage I are annular; the fuel flow channels II are uniformly distributed along the radial direction of the tail end of the fuel flow channel I, and the fuel flow channel I and the fuel flow channel II form a fuel flow channel; the oxidant flow channel II is uniformly distributed along the radial direction of the tail end of the oxidant flow channel I, and the oxidant flow channel I and the oxidant flow channel II form an oxidant flow channel; the combustion chamber cavity is positioned between a plane in which the fuel flow channel II is distributed and a plane in which the oxidant flow channel II is distributed, one end of the fuel flow channel II is communicated with the fuel flow channel I, and the other end of the fuel flow channel II is communicated with the combustion chamber cavity through a fuel nozzle; one end of the oxidant flow passage II is communicated with the oxidant flow passage I, and the other end of the oxidant flow passage II is communicated with the combustion chamber cavity through the oxidant nozzle; the rear end face of the combustion chamber cavity is uniformly provided with a plurality of inclined exhaust outlets, and each exhaust outlet is internally provided with a spray pipe;

The lateral fuel oil sealing cavity, the lateral oxidant sealing cavity, the front bearing seat and the bearing sleeve are sequentially fixedly connected with and sleeved on the main shaft along the axial direction of the main shaft; the lateral fuel seal cavity is positioned between the inner solid section and the middle thin-wall section of the main shaft, the lateral fuel seal cavity is provided with a radial fuel inlet, and fuel enters the lateral fuel seal cavity from the fuel inlet and then sequentially passes through a first fuel runner, a second fuel runner and a fuel nozzle to enter the combustion chamber cavity; the lateral oxidant sealing cavity is positioned between the middle thin-wall section and the outer thin-wall section of the main shaft, is provided with an oxidant inlet along the radial direction, and is filled with oxidant from the oxidant inlet and then sequentially enters the combustion chamber cavity through the oxidant flow passage I, the oxidant flow passage II and the oxidant nozzle; the fuel oil and the oxidant are sprayed out through the nozzle and collide with each other to be atomized for spontaneous combustion and ignition, high-temperature fuel gas is fully combusted in the cavity of the combustion chamber and accelerated through the obliquely arranged spray pipe, tangential thrust is generated, and the fuel gas exhaust and the main shaft generate a certain angle, so that tangential thrust components are generated due to the angle, and the main shaft is driven to rotate.

Further, the inner surfaces of the middle thin-wall section and the outer thin-wall section of the main shaft are respectively provided with axial oil grooves uniformly distributed along the circumferential direction.

Further, the cross-sectional diameter of the inner cavity of the spray pipe is firstly reduced and then increased.

Further, the number of the spray pipes is 3.

Further, the number of the fuel flow channels II and the number of the oxidant flow channels II are six.

The beneficial effects of the invention are as follows:

(1) The rotary gas generator of the invention eliminates the turbo pump, the combustion chamber and the nozzle of the traditional liquid fuel engine and combines the same into a structure, thereby being a simpler and more compact engine with higher thrust-weight ratio.

(2) The rotary gas generator takes self-contained propellant as a working medium, and the propellant is a double-component propellant, is not limited to the double-component propellant, and can also be a single-component propellant or a three-component propellant. The double-component propellant can be self-ignited by contact and collision without an additional ignition system, so that the weight of the system can be reduced and the working reliability of the system can be improved.

(3) Before entering the rotary gas generator, the propellant of the rotary gas generator passes through an oil conveying shaft, and the oil conveying shaft is arranged on the axis of an engine and rotates synchronously with the engine; in order to ensure the uniform distribution of the fuel oil conveyed to the rotary gas generator in the circumferential direction, an oil homogenizing groove is arranged on the inner wall surface of the oil conveying shaft.

(4) The rotary gas generator simultaneously realizes the integration of the gas generator and the shaft work output, has no turbine structure, simplifies the heat protection and realizes the integrated design.

Drawings

FIG. 1 is a schematic view of a rotary gas generator of the present invention;

FIG. 2 is a front cross-sectional view of the rotary gas generator of the present invention;

fig. 3 is a schematic diagram of a spindle 501.

Fig. 4 is a section A-A of fig. 2.

Fig. 5 is a cross-sectional view of fig. 2 taken along line C-C.

Fig. 6 is a sectional view of B-B in fig. 2.

Fig. 7 is a sectional view of the spout 6.

Fig. 8 is a cross-sectional view of the spindle 501.

In the figure, a lateral fuel seal cavity 1, a lateral oxidant seal cavity 2, a front bearing seat 3, a bearing sleeve 4, a combustion chamber body 5, a spray pipe 6, a fuel inlet 101, an oxidant inlet 201, a main shaft 501, a fuel runner I502, a fuel runner II 503, an oxidant runner I504, an oxidant runner II 505, a fuel nozzle 506, an oxidant nozzle 507, a combustion chamber cavity 508, an exhaust outlet 509 and an oil groove 510.

Detailed Description

The objects and effects of the present invention will become more apparent from the following detailed description of the preferred embodiments and the accompanying drawings, it being understood that the specific embodiments described herein are merely illustrative of the invention and not limiting thereof.

As shown in fig. 1 and 2, the rotary gas generator without turbine shaft work output of the invention comprises a lateral fuel oil sealing cavity 1, a lateral oxidant sealing cavity 2, a front bearing seat 3, a bearing sleeve 4, a combustion chamber body 5 and a spray pipe 6.

The combustion chamber body 5 includes a main shaft 501 extending out and a combustion chamber cavity 508 provided therein. The main shaft 501 is a stepped concentric sleeve shaft, as shown in fig. 3, and includes an inner solid section, a middle thin-wall section and an outer thin-wall section that are sleeved together. As shown in fig. 2, a first fuel flow passage 502 is formed in the middle thin-wall section, a first oxidant flow passage 504 is formed in the outer thin-wall section, and the first fuel flow passage 502 and the first oxidant flow passage 504 are both annular. The second fuel flow channels 503 are uniformly distributed radially along the end of the first fuel flow channels 502, the two components form a fuel flow passage; the oxidant runner two 505 is uniformly distributed along the radial direction of the end of the oxidant runner one 504, and the two constitute the oxidant runner. The combustion chamber cavity 508 is positioned between the plane in which the second fuel flow channel 503 is distributed and the plane in which the second oxidant flow channel 505 is distributed, one end of the second fuel flow channel 503 is communicated with the first fuel flow channel 502, and the other end of the second fuel flow channel is communicated with the combustion chamber cavity 508 through the fuel nozzle 506; one end of the oxidant flow channel II 505 is communicated with the oxidant flow channel I504, and the other end is communicated with the combustion chamber cavity 508 through the oxidant nozzle 507. As shown in fig. 4 and 5, the rear end surface of the combustion chamber 508 is further provided with three inclined exhaust outlets 509, each of which is provided with a nozzle 6.

As shown in fig. 5 and 6, in this embodiment, the number of fuel runners two 503 and the number of oxidant runners two 505 are six, and the number of nozzles 6 is 3. The specific number of the components can be set according to actual needs, and the components can be uniformly distributed. As shown in fig. 7, the cross-sectional diameter of the internal cavity of the nozzle 6 becomes smaller and then larger, requiring the high temperature fuel gas to pass through its throat at a local sonic velocity, and after passing through the throat at a supersonic velocity, and generating sufficient tangential thrust to drive the compressor in rotation and to provide sufficient pressure to the fuel.

The lateral fuel oil sealing cavity 1, the lateral oxidant sealing cavity 2, the front bearing seat 3 and the bearing sleeve 4 are sequentially arranged on the main shaft 501 along the axial direction of the main shaft 501 through the bearing sleeve. The flange plates of the lateral fuel oil sealing cavity 1 and the lateral oxidant sealing cavity 2 are fixedly connected together through bolts, the insides of the front bearing seat 4 and the bearing sleeve 5 are also respectively arranged on the outer thin-wall section of the main shaft 501 through bearings, and the lateral oxidant sealing cavity 2, the front bearing seat 3 and the bearing sleeve 4 are fixedly connected through bolts.

The lateral fuel seal cavity 1 is located between the inner solid section and the middle thin-wall section of the main shaft 501, the lateral fuel seal cavity 1 is provided with a radial fuel inlet 101, and fuel enters the combustion chamber cavity 508 from the fuel inlet 101 into the lateral fuel seal cavity 1, and then sequentially passes through the first fuel runner 502, the second fuel runner 503 and the fuel nozzle 506. The lateral oxidant seal cavity 2 is located between the middle thin-wall section and the outer thin-wall section of the main shaft 501, the lateral oxidant seal cavity 2 is provided with a radial oxidant inlet 201, and oxidant enters from the oxidant inlet 201 and then sequentially enters the combustion chamber cavity 508 through the oxidant runner I504, the oxidant runner II 505 and the oxidant nozzle 507.

The fuel oil and the oxidant are sprayed out through the nozzle and collide, atomized and self-ignited, and fully combusted in the combustion chamber cavity 508 to generate high-temperature fuel gas, the high-temperature fuel gas is accelerated through the obliquely arranged spray pipe 6 to generate tangential thrust, and the fuel gas exhaust and the main shaft 501 generate a certain angle a, so that tangential thrust components are generated due to the angle, and the main shaft 501 is driven to rotate.

Further, as shown in fig. 8, in order to ensure that the fuel oil delivered to the rotary thrust chamber is uniformly distributed in the circumferential direction, the inner surfaces of the middle thin-wall section and the outer thin-wall section of the main shaft 501 are respectively provided with axial oil grooves 510 uniformly distributed in the circumferential direction.

The rotary gas generator of the invention improves the energy efficiency of a propulsion system and improves the fuel economy under the condition of minimum propellant consumption. The turbine temperature limit can effectively solve the serious restriction problem of the thermodynamic cycle efficiency by the output shaft function of the turbine, so that the working temperature of the gas generator is increased, and the thermodynamic cycle efficiency of the engine is further improved; the turbine pump, combustion chamber and nozzle of the traditional liquid fuel engine are removed, and the turbine pump, combustion chamber and nozzle can be combined with a compressor to form a simpler and more compact engine with higher thrust-weight ratio.

It will be appreciated by persons skilled in the art that the foregoing description is a preferred embodiment of the invention, and is not intended to limit the invention, but rather to limit the invention to the specific embodiments described, and that modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for elements thereof, for the purposes of those skilled in the art. Modifications, equivalents, and alternatives falling within the spirit and principles of the invention are intended to be included within the scope of the invention.

Claims

1. The rotary gas generator without the turbine shaft power output is characterized by comprising a lateral fuel oil sealing cavity, a lateral oxidant sealing cavity, a front bearing seat, a bearing sleeve, a combustion chamber body and a spray pipe;

The combustion chamber body comprises a main shaft which extends out and a combustion chamber cavity which is internally arranged; the main shaft is a stepped concentric shaft sleeve shaft and comprises an inner solid section, a middle thin-wall section and an outer thin-wall section which are sleeved together; a fuel flow passage I is formed in the middle-layer thin-wall section, an oxidant flow passage I is formed in the outer-layer thin-wall section, and the fuel flow passage I and the oxidant flow passage I are annular; the fuel flow channels II are uniformly distributed along the radial direction of the tail end of the fuel flow channel I, and the fuel flow channel I and the fuel flow channel II form a fuel flow channel; the oxidant flow channel II is uniformly distributed along the radial direction of the tail end of the oxidant flow channel I, and the oxidant flow channel I and the oxidant flow channel II form an oxidant flow channel; the combustion chamber cavity is positioned between a plane in which the fuel flow channel II is distributed and a plane in which the oxidant flow channel II is distributed, one end of the fuel flow channel II is communicated with the fuel flow channel I, and the other end of the fuel flow channel II is communicated with the combustion chamber cavity through a fuel nozzle; one end of the oxidant flow passage II is communicated with the oxidant flow passage I, and the other end of the oxidant flow passage II is communicated with the combustion chamber cavity through the oxidant nozzle; the rear end face of the combustion chamber cavity is uniformly provided with a plurality of inclined exhaust outlets, and each exhaust outlet is internally provided with a spray pipe;

2. The rotary gas generator without turbine shaft power output according to claim 1, wherein the inner surfaces of the middle thin-wall section and the outer thin-wall section of the main shaft are respectively provided with axial oil grooves uniformly distributed along the circumferential direction.

3. The vortex free shaft work output rotary gas generator of claim 1 wherein the cross-sectional diameter of the internal cavity of the lance becomes smaller before larger.

4. The vortex free shaft work output rotary gas generator of claim 1 wherein the number of nozzles is 3.

5. The vortex free shaft work output rotary gas generator of claim 1 wherein the fuel flow passage two and the oxidant flow passage two are six.