An aircraft derivative gas turbine engine compressor inlet device

Abstract

This utility model belongs to the field of gas turbine technology, and specifically relates to an air intake device for an aero-derivative gas turbine compressor. The air intake device includes an intake casing, characterized in that: a shroud is fixed inside the intake casing, an inlet rectifier cone is fixed outside the intake casing, a cleaning pipeline is installed on the inlet rectifier cone, and a hydraulic motor drive and lubrication assembly is installed in the inner ring of the intake casing. The hydraulic motor drive and lubrication assembly is enclosed within the shroud, and its pipeline is connected to the hydraulic motor drive and lubrication assembly pipeline. The beneficial effects of this utility model are: it achieves gas turbine intake rectification, avoids leakage of parts affecting intake efficiency, and reduces intake resistance. By accelerating and uniformly introducing external air into the compressor first stage through a tapered channel, it reduces airflow separation, ensures that air enters the compressor flow path smoothly along the axial direction, and avoids compressor efficiency reduction or surge due to uneven flow velocity.

Description

Technical Field

[0001] This utility model belongs to the field of gas turbine technology, and specifically relates to an air intake device for a gas turbine compressor. Background Technology

[0002] Aero-engine to ground-based gas turbine (referred to as "aero-to-gas turbine") is a technology that transforms mature aero-engines into ground-based gas turbines through structural modifications and system optimization. This technology combines the high efficiency and lightweight advantages of aero-engines with the stable output characteristics of ground-based gas turbines, making it an important power solution for the energy, defense, and transportation sectors.

[0003] The air intake device (intake casing) of the aero-engine compressor is a key component at the front end of the engine. It is responsible for guiding and regulating the airflow entering the engine, and also undertakes functions such as structural support, anti-icing, and lubrication system integration. Some aero-engine intake casings are also connected to accessory drive casings. They are mostly made of aluminum alloy or titanium alloy and are designed for lightweighting.

[0004] Converting an aircraft engine into a ground-based gas turbine requires removing the accessory transmission housing, changing the front bearing, and redesigning an intake device that integrates intake rectification, structural support, lubrication, transmission, and cleaning systems, based on actual needs. Utility Model Content

[0005] To overcome the shortcomings of the prior art, this utility model provides an air intake device for the compressor of an aero-derivative gas turbine.

[0006] This utility model is achieved through the following technical solution: An intake device for an aero-derivative gas turbine compressor includes an intake casing, characterized in that: a fairing is fixed inside the intake casing, an inlet rectifier cone is fixed outside the intake casing, a cleaning pipeline is installed on the inlet rectifier cone, a hydraulic motor drive and lubrication assembly is installed in the inner ring of the intake casing, the hydraulic motor drive and lubrication assembly is enclosed in the fairing, and the hydraulic motor drive and lubrication assembly is connected to the hydraulic motor drive and lubrication assembly pipeline.

[0007] The fairing consists of a fairing head, a fairing fixing rod, a fairing bracket, and a fairing cylinder. The fairing head is fixed to the front end of the fairing bracket by the fairing fixing rod. The fairing cylinder is wrapped around the outside of the fairing bracket. The fairing bracket is fixed to the inner flange of the intake casing by the fairing flange.

[0008] Several cleaning nozzles are installed on the cleaning pipeline.

[0009] The hydraulic motor drive and lubricating oil assembly pipelines are mounted on the bracket.

[0010] The beneficial effects of this utility model are: by adopting the intake device structure design of this utility model, the intake rectification of the gas turbine is realized, the external leakage of parts is avoided from affecting the intake efficiency, and the intake resistance is reduced. The intake casing is located at the front end of the compressor. It accelerates the outside air through a tapered channel and introduces it evenly into the compressor first stage. This reduces airflow separation and ensures that the air enters the compressor flow passage smoothly along the axial direction, avoiding compressor efficiency reduction or surge caused by uneven flow velocity.

[0011] The intake casing integrates the gas turbine's hydraulic starting transmission system, front bearing, lubrication oil assembly, and cleaning pipelines, realizing functions such as transmission, structural support, lubrication, and cleaning. While retaining basic functions, the structural layout is reasonable, the functions are abundant, and the design meets the requirements of airflow and structure. Attached Figure Description

[0012] The present invention will be further described below with reference to the accompanying drawings.

[0013] Appendix Figure 1 This is a schematic diagram of the structure of this utility model; Appendix Figure 2 This is a schematic diagram of the fairing structure of this utility model; Appendix Figure 3 This is a schematic diagram of the inlet rectifier cone structure of this utility model; Appendix Figure 4 This is a schematic diagram of the intake casing structure of this utility model; Appendix Figure 5 This is a schematic diagram of the hanging bracket structure of this utility model; Appendix Figure 6 This is a schematic diagram of the cross-sectional structure of the hanging bracket of this utility model; In the diagram, 1 is the intake casing, 2 is the fairing, 3 is the inlet fairing cone, 4 is the cleaning pipeline, 5 is the hydraulic motor drive and lubrication assembly, 6 is the hydraulic motor drive and lubrication assembly pipeline, 7 is the fairing head, 8 is the fairing fixing rod, 9 is the fairing bracket, 10 is the fairing cylinder, 11 is the fairing flange, 12 is the cleaning nozzle, and 13 is the hanger. Detailed Implementation

[0014] The attached figure shows a specific embodiment of this utility model. This embodiment includes an intake casing 1, a fairing 2 fixed inside the intake casing 1, an inlet fairing cone 3 fixed outside the intake casing 1, a cleaning pipe 4 installed on the inlet fairing cone 3, and a hydraulic motor drive and lubrication assembly 5 installed in the inner ring of the intake casing 1. The hydraulic motor drive and lubrication assembly 5 is enclosed in the fairing 2, and the hydraulic motor drive and lubrication assembly 5 is connected to the hydraulic motor drive and lubrication assembly pipe 6.

[0015] The fairing 2 consists of a fairing head 7, a fairing fixing rod 8, a fairing bracket 9, and a fairing cylinder 10. The fairing head 7 is fixed to the front end of the fairing bracket 9 by the fairing fixing rod 8. The fairing cylinder 10 is wrapped around the outside of the fairing bracket 9. The fairing bracket 9 is fixed to the inner flange of the intake casing 1 by the fairing flange 11.

[0016] Several cleaning nozzles 12 are installed on the cleaning pipeline 4. The hydraulic motor drive and lubricating oil assembly pipeline 6 is installed on the bracket 13.

[0017] The intake device for the compressor of the aero-derivative gas turbine using this utility model consists of a fairing 2, an inlet rectifier cone 3, a mounting bracket 13, and an intake casing 1. The fairing 2 has the following structure: the fairing bracket 9 is fixed to the inner flange of the intake casing 1 by the fairing flange 11, the fairing head 7 is fixed to the front end of the fairing bracket 9 by the fairing fixing rod 8, and the fairing cylinder 10 is wrapped around the outside of the fairing bracket 9.

[0018] A cleaning pipe 4 is installed on the inlet rectifier cone 3. The inlet rectifier cone 3 is fixed to the outer flange of the intake casing 1 via the rear flange. Eight cleaning nozzles 12 are installed on the cleaning pipe 4 for compressor cleaning. The shroud 2 and the inlet rectifier cone 3 smoothly guide the external airflow into the engine intake casing, reducing turbulence and drag.

[0019] The hydraulic motor drive and lubrication assembly 5, along with the front bearing, are installed within the inner ring of the intake casing 1. The hydraulic motor drive assembly is connected to the front end of the compressor rotor via a coupling, hydraulically driving the gas turbine's cold run and start-up operations. The lubrication assembly ensures the supply and return of oil to the front bearing. The intake casing 1 is equipped with adjustable guide vanes for the gas turbine intake. As the front support point of the gas turbine, the intake casing 1 supports the compressor rotor and transmits radial and axial loads. The flow channel of the intake casing 1 is a convergent channel, balancing velocity and pressure changes to prevent flow separation and uneven velocity that could lead to reduced compressor efficiency or surge. The hydraulic motor drive and lubrication assembly 5 is enclosed within the fairing 2, preventing external leakage of intake components from affecting intake efficiency.

[0020] The hydraulic motor and lubricating oil assembly pipeline 6 is connected to the lubricating oil system at the bottom of the gas turbine via the bracket 13. The cross-section of the bracket 13 is as shown in Figure 6. Figure 6 As shown, it features a streamlined design, which avoids external leakage of pipes that could affect air intake efficiency.

[0021] The novel intake device design, achieved by modifying the structural support and transmission methods of the aforementioned aero-engine converted into a ground-based gas turbine, enables gas turbine intake rectification, preventing external component leakage from affecting intake efficiency and reducing intake resistance. Located at the front of the compressor, the intake casing accelerates and evenly guides external air into the compressor's first stage via a converging channel, reducing airflow separation and ensuring smooth axial entry of air into the compressor's flow path. This prevents compressor efficiency degradation or surge due to uneven flow velocity. Simultaneously, the intake casing integrates the gas turbine's hydraulic starting transmission system, front bearing, lubrication components, and cleaning pipelines, realizing functions such as transmission, structural support, lubrication, and cleaning. While retaining basic functions, the structural layout is rational, functionally rich, and the design meets airflow and structural requirements.

Claims

1. An air intake device for a gas turbine compressor, comprising an air intake casing (1), characterized in that: The intake casing (1) has a fixed shroud (2) inside and an inlet rectifier cone (3) fixed outside. A cleaning pipe (4) is installed on the inlet rectifier cone (3). A hydraulic motor drive and lubrication assembly (5) is installed in the inner ring of the intake casing (1). The hydraulic motor drive and lubrication assembly (5) is wrapped inside the shroud (2). The hydraulic motor drive and lubrication assembly (5) is connected to the hydraulic motor drive and lubrication assembly pipe (6).

2. The intake device for the compressor of an aero-derivative gas turbine according to claim 1, characterized in that: The fairing (2) consists of a fairing head (7), a fairing fixing rod (8), a fairing bracket (9), and a fairing cylinder (10). The fairing head (7) is fixed to the front end of the fairing bracket (9) by the fairing fixing rod (8). The fairing cylinder (10) is wrapped around the outside of the fairing bracket (9). The fairing bracket (9) is fixed to the inner flange of the intake casing (1) by the fairing flange (11).

3. The intake device for the compressor of an aero-derivative gas turbine according to claim 1, characterized in that: Several cleaning nozzles (12) are installed on the cleaning pipeline (4).

4. The intake device for the compressor of an aero-derivative gas turbine according to claim 1, characterized in that: The hydraulic motor drive and lubricating oil assembly pipeline (6) is installed on the bracket (13).

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