JPS62157208A - Multiple type valve mechanism - Google Patents

Abstract

PURPOSE:To achieve the weight reduction of an engine by rolling a roller interlocked with an actuator inside grooves for a plural number of a valve levers, in a duplex type valve mechanism for controlling the tip clearance of gas turbine blades. CONSTITUTION:A roller 15 interlocked with an actuator is rolled inside grooves for a high-pressure turbine valve lever 13 and a low-pressure turbine valve lever 14. These grooves are made to have a crooked shape, and while the valve lever on one side is fixed, the valve lever on the other side is enabled to move. Thus, since a plural number of valves can be driven by one actuator and one system of piping can be eliminated, the weight of an engine can be reduced.

Description

DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention generally relates to a multiple valve mechanism in which several actuators drive several valves independently or in conjunction with each other depending on the purpose. In particular, the present invention is suitable as a dual valve mechanism for controlling the blade tip clearance of a gas turbine engine.

Conventional technology In recent years, large gas turbine engines for aviation have been using valves to control the air drawn from the compressor section to improve fuel consumption, and the air is blown onto the surface of the turbine case to cool it, making it suitable for flight conditions. A method for adjusting the gap between turbine blade tips has been put into practical use.

In a two-shaft gas turbine engine that has a high-pressure turbine and a low-pressure turbine, the high-pressure turbine blade clearance has a greater influence on the fuel consumption rate than the low-pressure turbine blade clearance, so the former is normally controlled continuously, and the latter is controlled in two stages (fully open).・Completely closed) control, and each has an independent valve actuation device.

This will be explained with reference to FIG. Cooling manifold pipe 03 for high pressure turbine tip clearance control for high pressure turbine 01
The compressed air introduced from the compressed air inlet 008 is controlled steplessly by a butterfly valve 06. This control is performed hydraulically via a link 010 by controlling an actuator 011 with an electronic control section 09.

Also, the compressed air population 07 introduced into the cooling manifold pipe 04 for low pressure turbine tip clearance control for the low pressure turbine 04
The compressed air from is opened and closed by a poppet valve 05. This control is performed pneumatically by controlling the lenoid valve 012 using the electronic control section 09.

Problems to be Solved by the Invention In the conventional system as described above, the high-pressure system and the low-pressure system are completely separated, and cannot necessarily be said to be the best in terms of weight, space occupied, and cost.

Means for Solving the Problems The present invention has been made to improve the conventional system described above, and generally includes a multiple valve mechanism in which one actuator drives a plurality of valves independently or in conjunction with each other. wherein the valve levers are arranged so that rollers that move in a straight line according to the movement of the actuator roll in grooves provided in the valve levers respectively fixed to the plurality of valve shafts,
By forming these grooves into curved grooves, the valve mechanism has a groove shape that is parallel to the linear motion of the roller in a specific operating range.

If the present invention is applied to the above-mentioned dual valve mechanism for controlling the tip clearance of the gas turbine engine, the control valves for the high-pressure turbine and the low-pressure turbine can be controlled by one control power unit (actuator) to meet the above-mentioned purpose. It is what makes it possible to operate.

Embodiment FIG. 1 shows the overall concept of a high-pressure and low-pressure turbine blade tip clearance control device. Figures 2a-2d show a cam mechanism for driving a double screw valve according to the invention. FIG. 3 shows the relationship between the opening degrees of one actuator and two valves obtained by this valve structure.

As is clear from FIG. 1, according to the present invention, the air introduction pipe 3
A high-pressure turbine butterfly valve 4 is installed in the pipe line from the air intake pipe 3 to the high-pressure turbine case cooling pipe 7, and a low-pressure turbine butterfly valve 5 is installed in the pipe line from the air introduction pipe 3 to the low-pressure turbine case cooling pipe 8. , respectively. These spiral valves4.
5 is controlled by a cam mechanism 6 provided at the tip of a bushing rod 2 that is linearly moved by a control power unit 1.

FIG. 2a shows a concrete example of this cam mechanism.

As is clear from this figure, there is a lever drive roller 15 at the tip.
A bushing rod 16 to which is fixed is arranged so as to move linearly. This bushing rod 16 is biased forward by a fail-safe spring 17, which will be described later, and its linear motion is controlled by the driving power unit 1 shown in FIG.

The lever driving roller 15 is connected to the high pressure turbine side valve lever 13.
It slides in the bent groove of the low pressure turbine side valve lever 14, and also slides in the bent groove of the low pressure turbine side valve lever 14. High pressure turbine side valve lever 1
3 is fixed to 1i [1] 11 for high pressure turbine,
The low pressure turbine side valve lever 12 is a low pressure turbine valve shaft 12
is fixed.

The solid line positions of the roller 15 and the valve lever 13.14 in FIG. 2a correspond to point DK in FIG. 3, and the positions in FIG. 2b correspond to point DK in FIG.
The position in FIG. 2C corresponds to point B in FIG. 3, and the position in FIG. 2d corresponds to point E in FIG. 3.

In FIG. 3, the bushing rod 16 is moved from point A to point B (second c).
By operating K, the low-pressure turbine butterfly valve 5 changes from fully closed to 70 degrees open, and during this time the high-pressure turbine spiral valve 4 remains fully closed.

Further, when actuated to point C (position in Fig. 2b), the butterfly valve 5 for the low pressure turbine is fully opened, and the butterfly valve 4 for the high pressure turbine is 25% open. The range from point 0 (position in Figure 2b) to point D (position in Figure 2a) is a range in which only the butterfly valve 4 for the high pressure turbine is controlled to an appropriate valve opening while the butterfly valve 5 for the low pressure turbine remains fully open. It is. Point E (position in Figure 2d) is the control power plant 1
(Fig. 1) etc. is in a position where it automatically stops by the force of the spring 17 (Fig. 2a).
is opened by 40 degrees, and the high-pressure turbine butterfly valve 4 is fully closed, which is provided for the so-called fail-safe purpose of maintaining safe engine operation.

As shown in the above specific examples, the feature of the present invention is that one of the curved grooves provided in the lever fixed to the valve stem of the two valves has a straight line shape in a certain part of the roller rolling in the groove. This allows one valve to remain fixed while the other valve can be controlled to match the movement.

In addition to those shown in the specific examples, a cam device in which a single actuator drives several valves independently or in conjunction with each other depending on the purpose can be easily realized by applying the present invention.

Effects of the Invention By adopting the present invention, it is possible to reduce the number of independent valve drive devices (actuators) for the low-pressure turbine and high-pressure turbine to one system, as well as the associated piping, etc., which not only reduces costs. It can contribute to reducing the weight of aircraft engines.

[Brief explanation of drawings]

FIG. 1 is a schematic diagram showing the arrangement of a high-pressure turbine and a low-pressure turbine blade tip clearance control device to explain the present invention in detail;
The figure is a sectional view showing details of the cam mechanism, Figure 2b, Figure 2.
Figures c and 2d are similar views showing the relationship between the bushing rod and the cam position, Figure 3 is a graph showing the relationship between the valve opening and the stroke of the bushing rod, and Figure 4 is a graph showing the blade of a conventional gas turbine engine. It is a schematic diagram showing a tip clearance control mechanism. 01--High pressure turbine, 02...Low pressure turbine, 03...
・Cooling manifold pipe for high pressure turbine tip clearance control, 04
・Cooling manifold pipe for low pressure turbine tip clearance control, 0
5...Poppet valve, 06...Butterfly valve, 07,08
・・Compressed air inlet, 09・・Electronic control unit, 010・・Link, 011・・Actuator, 012・・Nlenoid valve, ■・・・Power unit for [Jij iM], 2・・Punyurod, 3・・Air introduction Pipe, 4. Butterfly valve for high pressure turbine, 5. Butterfly valve for low pressure turbine, 6. Cam mechanism, 7
...High pressure turbine case cooling pipe, 8..Low pressure turbine cooling pipe, 11..Valve shaft for high pressure turbine/, 12..Valve shaft for low pressure turbine, 13..High pressure turbine side valve lever, 14..
・Low-pressure turbine side valve lever, 15... v-bar m motion roller, 16... bush rod, 17 fail-safe spring. Sub-agent Masami Kimura (and 7 others)

Claims (1)

[Claims] In a multiple valve mechanism in which a single actuator drives a plurality of valves independently or in conjunction, a roller that moves in a straight line according to the movement of the actuator is provided on a valve lever fixed to each of the plurality of valve shafts. By arranging these valve levers so as to roll in the grooves and making these grooves curved, the groove shape is made parallel to the linear motion of the roller in a specific operating range, and this A multiple valve mechanism characterized in that a valve related to a valve lever is fixed while controlling other valves.