CN113914998B

CN113914998B - Combined compression gas turbine engine

Info

Publication number: CN113914998B
Application number: CN202111298216.7A
Authority: CN
Inventors: 黄兴; 陈璇; 罗潇; 丁金涛; 曹俊; 李维
Original assignee: Hunan Aviation Powerplant Research Institute AECC
Current assignee: Hunan Aviation Powerplant Research Institute AECC
Priority date: 2021-11-04
Filing date: 2021-11-04
Publication date: 2022-10-14
Anticipated expiration: 2041-11-04
Also published as: CN113914998A

Abstract

The invention discloses a combined compression gas turbine engine, and belongs to the technical field of gas turbine engines. The compressor comprises a turbine rotor and a differential planetary gear box, wherein the differential planetary gear box drives an inlet-stage centrifugal impeller and an inlet-stage axial diffuser with blades, the turbine rotor directly drives an outlet-stage centrifugal impeller through a gas turbine shaft, the driven outlet-stage centrifugal impeller, the driven inlet-stage centrifugal impeller and the driven inlet-stage axial diffuser with blades can rotate to apply work to compress incoming flow, the incoming flow is driven by a differential planetary reducer to form three different rotating speeds of a front-row centrifugal impeller, an axial diffuser and a rear-row centrifugal compressor, the rotating speed ratio between the front-row centrifugal impeller, the axial diffuser and the rear-row centrifugal compressor is not a fixed value, the oil consumption rate of an engine is further reduced by designing a compression system with higher efficiency, and an ultra-compact combined compression mode of the inlet-stage centrifugal impeller, the axial diffuser and the outlet-stage centrifugal compressor is formed.

Description

Combined compression gas turbine engine

Technical Field

The invention belongs to the technical field of gas turbine engines, and particularly relates to a combined compression gas turbine engine.

Background

One prior art gas turbine engine is shown in fig. 2 (dual centrifugal compressor). The rotating turbine and the compressor are connected on the same shaft, a heat source is arranged between the turbine and the compressor, air is continuously sucked into the compressor, compressed air enters a combustion chamber to be injected and combusted into high-temperature gas, then the high-temperature gas enters the turbine to do work through expansion, and the expansion work is transmitted to the compressor through a transmission shaft, so that the continuous work of an engine is realized.

The disadvantages of the existing gas turbine engines are: due to the limitation of materials, the pressure ratio of the double centrifugal compressors widely applied to the compression systems of small and medium-sized gas turbine engines is difficult to further improve; in order to meet the requirement of further reduction of the oil consumption rate, a compression system with a higher pressure ratio and a multistage axial flow/centrifugal combination or a full axial flow or multi-shaft driving is generally adopted, so that the size and the weight of a gas compressor are increased rapidly, the stroke of a gas compression flow passage is longer, and a more complex shafting structure is caused, and the low efficiency of the compression system directly causes that the power-to-weight ratio and the oil consumption rate of the existing gas turbine engine cannot meet the requirement of a future aircraft.

Disclosure of Invention

It is an object of the present invention to provide a combined compression gas turbine engine to address at least one of the problems and deficiencies set forth in the above background.

According to one aspect of the present invention, there is provided a combined compression gas turbine engine comprising a turbine rotor, a gas turbine shaft, an outlet stage centrifugal impeller and an inlet stage vaned axial diffuser, further comprising: the differential planetary gearbox drives the inlet-stage centrifugal impeller and the inlet-stage axial diffuser with blades, the turbine rotor directly drives the outlet-stage centrifugal impeller through a gas turbine shaft, so that the driven outlet-stage centrifugal impeller, the driven inlet-stage centrifugal impeller and the driven inlet-stage axial diffuser with blades can rotate to apply work to compress incoming flow, the three different rotating speeds of the front-row centrifugal impeller, the axial diffuser and the rear-row centrifugal compressor are formed through the driving of the differential planetary reducer, the rotating speed ratio between every two centrifugal impellers is not a fixed value, and the oil consumption rate of the engine is further reduced by designing a compression system with higher efficiency.

Further, the differential planetary gearbox comprises sun gears, planet carriers and ring gears, a plurality of said planet gears being arranged within one or more ring gears for planetary rotation about one or more sun gears, a plurality of planet gears collectively driving one planet carrier.

Further, the turbine rotor is connected with an outlet-stage centrifugal impeller and a sun gear of a differential planetary gearbox through a gas turbine shaft.

Further, a planet carrier at the output end of the differential planetary gear box is connected with the inlet-stage centrifugal impeller.

Furthermore, a ring gear at the output end of the differential planetary gear box is connected with an inlet-stage axial diffuser with blades, so that the pressure ratio of the compression system is greatly increased under the condition that the size of the compression system is not increased, and the reduction of the oil consumption rate of an engine is facilitated.

Further, the sun gear, the planet carrier and the ring gear are coaxially arranged.

Further, the diameters of the planetary gears are all equal, and the axial lengths of the planetary gears are all equal.

Furthermore, the inlet-stage centrifugal impeller, the inlet-stage radial diffuser, the inlet-stage axial diffuser with blades, the transition section, the outlet-stage centrifugal impeller and the outlet-stage diffuser are sequentially connected and are coaxially arranged with the gas turbine shaft.

Compared with the prior art, the invention has the beneficial effects that:

on the basis of the existing single-rotor double-centrifugal-compressor gas turbine engine, a differential gear is adopted to drive a contra-rotating centrifugal compressor of a front-row conventional centrifugal impeller/axial diffuser (with blades) to replace a traditional compression system, so that a compressor which is compressed by a front-row centrifugal impeller, a front-row axial diffuser (with blades) and a rear-row centrifugal impeller in a combined manner with a non-fixed rotation speed ratio is formed, and the front-row contra-rotating centrifugal compressor fully utilizes the advantage of strong anti-prerotation working capacity to increase the pressure ratio of the compression system without increasing the axial size of the compression system;

meanwhile, the rotating speed ratio is not fixed, so that a larger space is brought to the performance adjustment and optimization, and a compression system with higher efficiency is designed to further reduce the oil consumption rate of the engine by utilizing the advantage of large space allowance. Therefore, the novel combined compression gas turbine engine greatly improves the power-weight ratio of the engine and reduces the oil consumption rate, thereby solving the problem that the traditional gas turbine engine is difficult to meet the modern long-range.

Drawings

To facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a schematic diagram of a prior art gas turbine engine employing dual centrifugal compressors;

FIG. 3 is a schematic view of a differential planetary gearbox.

In the figure: 110. an inlet stage centrifugal impeller; 111. an inlet stage radial diffuser; 112. an inlet stage axial diffuser with blades; 113. a transition section; 114. an outlet stage centrifugal impeller; 115. an outlet stage diffuser; 116. a reflow combustion chamber; 117. a turbine guide; 118. a turbine rotor; 119. a gas turbine shaft; 120. a differential planetary gear box; 121. a sun gear; 122. a planetary gear; 123. a planet carrier; 124. a ring gear.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention are further described in detail below by way of examples with reference to the accompanying drawings. In the specification, the same or similar reference numerals denote the same or similar components. The following description of the embodiments of the present invention with reference to the drawings is intended to explain the general inventive concept of the present invention and should not be construed as limiting a combined compression gas turbine engine of the present invention.

Furthermore, in the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. In other instances, well-known structures and devices are shown in schematic form in order to simplify the drawing.

According to a general technical concept of the present invention, as shown in fig. 1 to 3, there is provided a combined compression gas turbine engine, including a turbine rotor 118, a gas turbine shaft 119, an outlet stage centrifugal impeller 114, and an inlet stage bladed axial diffuser 112, wherein the inlet stage centrifugal impeller 110, the inlet stage radial diffuser 111, the inlet stage bladed axial diffuser 112, a transition section 113, the outlet stage centrifugal impeller 114, and the outlet stage diffuser 115 are sequentially distributed and coaxially disposed with the gas turbine shaft 119;

the differential planetary gearbox 120 comprises a sun gear 121, planet gears 122, a planet carrier 123 and a ring gear 124, a plurality of said planet gears 122 being arranged within the one or more ring gears 124 for planetary rotation about the one or more sun gears 121, each planet gear 122 being fixedly connected at its axial centre to the planet carrier 123 by a connecting shaft, the plurality of planet gears 122 driving in common one planet carrier 123, the sun gear 121 driving the planet gears 122 with central straight spur gear teeth, the interface being introduced with a small amount of backlash via tooth offset to ensure correct meshing. In the embodiment shown, there are 3 planet gears 122, and it is also possible and not limiting to 2, 4 or 5 planet gears 122 rotating planetarily around a sun gear 121, each planet gear 122 meshing with a ring gear 124.

The sun gear 121, the carrier 123 and the ring gear 124 are coaxially arranged, and each of the planet gears 122 is equal in diameter and equal in axial length.

Differential planet gears 122 planet carrier 123 and ring gear 124 are power outputs and sun gear 121 is a power input.

The gas turbine shaft 119 is welded to or integrally formed with a sun gear 121 of the differential planetary gear case 120, the outlet-stage centrifugal impeller 114 is mounted on the gas turbine shaft 119 in a centering manner, and the turbine rotor 118 is connected to the outlet-stage centrifugal impeller 114 and the sun gear 121 of the differential planetary gear case 120 via the gas turbine shaft 119.

The planet carrier 123 at the output end of the differential planetary gear box 120 is connected with the inlet-stage centrifugal impeller 110, the ring gear 124 at the output end of the differential planetary gear box 120 is connected with the inlet-stage axial diffuser 112 to form a mode that the turbine rotor 118 directly drives the outlet-stage centrifugal impeller 114 through the gas turbine shaft 119 and drives the inlet-stage centrifugal impeller 110 and the inlet-stage axial diffuser 112 through the differential planetary gear box 120, so that the driven three components can rotate to do work to compress incoming flow, the compressed air enters the backflow combustion chamber 116 to be injected with oil and combusted into high-temperature gas, and then enters the turbine through the turbine guider 117 to do work through expansion, and the expansion work is transmitted to the compressor through the gas turbine shaft 119 so as to realize the continuous work of the engine.

The working principle is as follows:

on the basis of the compression of the existing single-rotor double-centrifugal compressor, the differential planetary gear box 120 is adopted to respectively drive the front-row conventional centrifugal impeller and the axial diffuser with the blades, so that a novel combined compression gas turbine engine is formed. The compression system of the engine has the characteristics of compact structure, high efficiency and high pressure ratio. The novel compression mechanism adopts the form of the rotary pressurization of the axial diffuser to replace the traditional static diffuser under the condition of ensuring the structural size of the existing compression mechanism, utilizes the advantage of strong anti-prerotation acting capacity, and realizes the purpose of greatly improving the total pressure ratio of the centrifugal compressor under the condition of a compact structure.

The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A combined compression gas turbine engine comprising a turbine rotor (118), a gas turbine shaft (119) and a dual centrifugal compressor comprising an inlet stage centrifugal impeller (110), an outlet stage centrifugal impeller (114) and an inlet stage bladed axial diffuser (112), characterized in that it further comprises:

the differential planetary gear box (120), the differential planetary gear box (120) drives the inlet stage centrifugal impeller (110) and the inlet stage axial diffuser with blades (112), the turbine rotor (118) directly drives the outlet stage centrifugal impeller (114) through a gas turbine shaft (119), and the driven outlet stage centrifugal impeller (114), the driven inlet stage centrifugal impeller (110) and the driven inlet stage axial diffuser with blades (112) can rotate to do work to compress airflow; the differential planetary gear box (120) is used for driving, three different rotating speeds of the inlet-stage centrifugal impeller (110), the inlet-stage axial diffuser with blades (112) and the outlet-stage centrifugal impeller (114) are formed, and the rotating speed ratio between every two centrifugal impellers is not a fixed value.

2. A combined compression gas turbine engine according to claim 1, characterised in that the differential planetary gearbox (120) comprises a sun gear (121), planet gears (122), a planet carrier (123) and a ring gear (124), a plurality of said planet gears (122) being arranged within one or more ring gears (124) for planetary rotation around one or more sun gears (121), a plurality of planet gears (122) jointly driving one planet carrier (123).

3. A combined compression gas turbine engine according to claim 2, characterised in that the turbine rotor (118) is connected to the outlet stage centrifugal impeller (114) and the sun gear (121) of the differential epicyclic gearbox (120) by means of a gas turbine shaft (119).

4. A combined compression gas turbine engine according to claim 3, characterised in that the planet carrier (123) at the output of the differential epicyclic gearbox (120) is connected to the inlet stage centrifugal impeller (110).

5. The combined compression gas turbine engine as claimed in claim 4, characterised in that the ring gear (124) at the output of the differential epicyclic gearbox (120) is connected to an inlet stage bladed axial diffuser (112).

6. Combined compression gas turbine engine according to claim 5, characterized in that the sun gear (121), the planet carrier (123) and the ring gear (124) are arranged coaxially.

7. The combined compression gas turbine engine of claim 2, wherein the plurality of planet gears (122) are all equal in diameter and equal in axial length.

8. The combined compression gas turbine engine as claimed in claim 1, wherein the inlet stage centrifugal impeller (110), the inlet stage radial diffuser (111), the inlet stage bladed axial diffuser (112), the transition section (113), the outlet stage centrifugal impeller (114) and the outlet stage diffuser (115) are connected in series and are arranged coaxially to the gas turbine shaft (119).