JPS5865903A - Rotor for axial flow machine - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to rotor blades for axial fluid flow turbines or combustion turbines, and more particularly to rotor blades that can be retrofitted onto rotor disks originally created for uncooled turbine rotor blades. This relates to the cooling two rotor blades of a combustion turbine.

It is known that greater operating efficiency and power output of combustion turbines can be obtained by increasing the inlet operating temperature. However, the inlet operating temperature is limited by the maximum temperature that the rotating turbine blades can withstand. Furthermore,
As turbine blade temperatures increase as inlet gas temperature increases, the risk of blade damage from the stresses and tensions normally associated with blade rotation also increases.

Increasing the inlet operating temperature while keeping the turbine blade temperature below the maximum working temperature specified for the blade material, either by total cooling the turbine blades, by making the blades from an IT-thermal material, or both. I can do it.

There are currently many combustion turbines with uncooled rotor blades. In some types, the first stage vanes are cooled, but the vanes of subsequent stages are not. Typically,
Combustion turbines with uncooled rotor blades are disclosed in U.S. Pat. ,j'?
, No. 2,766. Blade cooling is a simple method for providing partial cooling of blade blades. U.S. Patent No. 3. S7,? In the structure disclosed in the '66 patent, cooling air from the compressor is directed through individual passages within each disk to the passage between the vanes and the disks. And now it is used for feathers.

To improve the operating efficiency and power output of combustion turbines, devices are provided to allow cooling air flow through the turbine blades themselves to ensure that the blade surfaces are cooled to a temperature below the turbine inlet temperature. It is desirable to do so.

A conventional approach to solving such problems is described in U.S. Patent No. 3. G! ; , 7. It is disclosed in the QJS specification. The patent specification describes a sealing assembly that seals the discharge end of a cooling passage between a blade and a disk to allow cooling air to pass upwardly within the blade and into the blade of a turbine blade. ing. After that, this cooling air exits the wing section and reaches a high temperature i.
Enter the jJ+Kagasu exhaust path. Such a sealing assembly consists of a seal structure that mates with a groove in the vane and the disk to close the discharge end of the cooling passage between the vane and the disk. However, the device disclosed in the U.S. patent specification can be used not only for turbine blades with a special VC configuration.
Special machining of the rotor disc is also required.

Although the previously described sealing assemblies provide an effective and efficient method of directing cooling air toward the turbine blades, they cannot be applied station-by-station in existing combustion turbines. Applying the structure requires structural improvements to both the turbine blades and the rotor disk. Modification of the rotor disk requires removal of the rotor shaft from the lower portion of the turbine casing. U.S. Patent No. 3.4'
9.7. ．． 2/; As explained in specification 1', the positioning of the rotor is extremely critical and once properly positioned it should be kept as stable as possible. Removal of the rotor shaft also requires time and expense f! to make changes to the combustion turbine. :To increase.

Therefore, we developed a cooled combustion turbine blade with a sealing structure that can be retrofitted onto existing rotor disks and provides the advantages of a six-cooled turbine blade without the drawbacks of requiring removal of the rotor shaft. It is desirable to do so.

Briefly stated, the present invention provides a cooling device and a seal.
Combustion turbine rotor blades that are not equipped with an F-device and supported on a rotor disk are provided as a replacement for uncooled turbine blades in existing combustion turbines. This turbine blade with cooling and sealing devices cooperates with the rotor disk to provide a blade cooling structure in existing disks with uncooled blades. The cooling device is provided in the blade blade portion and the root portion,
Consisting of devices for guiding cooling fluid through them. The sealing device is fixed to the vane and is configured to completely seal the axially extending space formed between the radially innermost portion of the vane and the rotor disk. Thereby, the sealing device closes the outlet for the cooling fluid and directs the cooling flow into the metal turbine blade.

Use of such cooled turbine blades does not require modification or removal of the turbine rotor assembly.

Because the operating temperatures of existing combustion turbines are variable, it has become necessary to provide cooled turbine blades where blades were not previously cooled. According to the invention, a combustion turbine blade is provided that includes a cooling device and a sealing device. The turbine blades of the present invention are suitable for being supported on and operating in conjunction with conventional turbine rotor disks and are suitable for blade cooling structures for existing turbines having uncooled bladed disks. give. This cooled turbine blade includes a cooling device H specifically configured to guide cooling fluid, and a blade 411! A sealing device is provided for closing the space or fluid passageway between the root and the disc of conventional construction, thereby allowing cooling fluid to flow within the improved turbine blade structure.

Referring to the accompanying drawings, FIG. 1 shows a portion of a typical conventional rotor 10 for an axial flow turbine in axial section. The rotor /θ consists of a rotor disc assembly, and in the drawing only two rotor discs /2.
The IQs are shown secured together by joints (retainers)/& placed around the periphery to extend through the disc. Only those sub-ports are shown in Figure 1.

Disc/;2. /da is the rotor blade extending radially outward therefrom/6. /gf respectively, and the wings are:
axially spaced, radially inwardly extending fixed stator or nozzle vanes 20. ．． 2/, ;12. Each row has two blades with a side entrance type root core A.
2g, the four prongs each having a tooth profile or fur tree suitable for placement in a tooth profile recess (see Figure 5) provided around the disk.
It can be anything in shape.

The rotor disks /, 2, /4' are further provided with axially extending holes or passages 30.3.2, respectively. These passages are located in the central Tokuda Village structure 3.
Tubular temporary part 4J, y arranged in a relationship surrounding Sf
It is in fluid communication with passageway 33 formed by lI.

Openings lθ extending in the radial direction are provided spaced apart in the circumferential direction around the disk, on the upstream side of llI, and in the vicinity of its periphery. An open log O is formed within the disk and is in fluid communication with passageway 33.

Furthermore, disk/2. On the upstream side of /'l, a radially outwardly facing fc annular continuous groove or passageway is provided. The groove is formed to extend radially and be in fluid communication with k'Bp log θ.

For details of this typical conventional construction, see U.S. Pat.
, 57.2.9 A Disclosed in Specification No. A.

FIG. 2 shows a portion of a conventional disk/2 having a turbine blade and sealing device constructed in accordance with the present invention. For purposes of the present invention, the disk periphery and 74
The structure of ' is substantially the same. Turbine blade/6
consists of a blade section 4'A and a root section λ6, and the root section of the turbine blade is defined by U.S. Pat.
- is fixed to the disc by a conventional side plate rim, Sθ, and a toothed structure at the vane-to-disc junction, as disclosed in US Pat. The upstream side plate 5θ arranged in the shape of a nucleus is formed on the disk and the blade, respectively.
When fixed within cHsa,sy, it cooperates with the adjacent end of the turbine blade root 2O to define a circumferentially continuous cooling fluid chamber 1I11t.

Chamber 471I has a continuous passage lI- and a radial opening l
The IO is configured in fluid communication with the IO.

When the rotor operates, pressurized cooling hole material such as air from the compressor section of the combustion turbine flows through the passage 33, @
/ is sent to disk /2 (see Figure 1). This first
At disk/co, the airflow is split, and the sB portion is II! in disk/2! llI flows through the path 30 in the pure direction to the th disk/4'. The residual airflow is directed radially outward toward the open log 0 below the annular groove.
It flows upward (as shown by the arrow in the figure). The air then passes from the annular groove 47.2 into the annular chamber formed by the upstream side plate and the ends of the vanes. next,
Air flows through the gap between the blade part and the disc recess, in particular into the space formed between the base of the vane part and the turbine disc, ie into the blennium chamber s6.

In the conventional typical structure shown in FIG. 7, cooling air is flowed from the plenum chamber 5 through one hole in the side plate g into the exhaust path of the high-temperature power gas for driving the turbine. However, in the cooling device according to the invention, the sealing device 5g shown in detail in FIGS. Passage 60 (into the guide device) extending into the passageway 60 (into the guiding device). In terms of 3i%, it is not an engineering school thing,
Any of a variety of known configurations may be used.

The pricking device 5g is rotor-task/for its application.
It is constructed so that the improvement of the structure of No. 2 (ii) etc. is not mandatory. Fig. 3 is a perspective view of the left side of the sealing device g, looking toward the upstream side; FIG.

The upper part of the sealing device 6.2 is shaped to fit continuously into the radially inner toothing 61I (see FIG. 5) of the turbine blade. Furthermore, the lower part 6 of the sealing device defines a rectangular notch 6, which is used for sealing into the root of the turbine blade. (See Figure S.) Shaped to closely fit and seal the downstream end of the plenum chamber. It should be of sufficient thickness to allow for the sealing, preferably less than or equal to the radial dimension of the lower part.A suitably shaped indentation 7.2 is provided on the surface adjacent to the side plate g for sealing. Recesses 4 and 72 provided in the lower part of the device facilitate the assembly and removal of the seals in the vaned rotor and blennium chambers.

The discharge end of the bottom tooth in the vane part is notched as indicated by the numeral 7 in Figure 2 to allow the lower part of the sealing device to fit tightly into the disc gingiva. 21
A tab 76 integral with the vane engages a rectangular notch 6 in the sealing section to limit axial movement of the sealing device. The tight fit of the seal within the disc teeth and plenum chamber limits radial movement of the seal.

Thus, the combination of cooperating cooled Talpit blades and sealing devices in accordance with the present invention provides a simple and effective structure that can be retrofitted to existing combustion turbines with uncooled blades. The turbine blade and its cooling device according to the invention described above make it possible to replace an uncooled turbine blade with a cooled turbine blade without disturbing the turbine rotor or making any structural modifications. be.

[Brief explanation of the drawing]

FIG. 1 is a sectional view showing a portion of a turbine section in a typical conventional combustion turbine; FIG. , FIG. 3 is a front perspective view of the sealing device according to the present invention, FIG. 7 is a side view of the sealing device according to the present invention, and FIG. S is a sectional view taken along the line V-V in FIG. ,
1 is an upstream view of the root and sealing device of a cooled turbine blade of the present invention in position within a turbine disk; FIG. 10. ・mouth~evening, /2. I'l - rotor disk,
/A, /l;...Rotor blade, 0.2/. 2λ...Nozzle blade 1.2A, 2g...Root, 30,
,? , 2... Passage, 33... Passage, 3q... Tubular rear member, 3S... Torque tube structure, tio... Radial opening (guide device), Coo... Passage (guide device), lda... - Coolant chamber, lI6... wing section, 47 &... side plate, SO... side plate, j, 2. j da... i#L-z... plenum room (space) sg-... sealing device, to... passage (guiding device) 6
da...teeth, 66...notch, bg...bottom of sealing device, 7
0... peripheral area, 7... depression, ? 'l...Discharge end, 7
6...Tab. Part 1 Figure 74 Figure 5 Shin Hii Figure 2 Figure 3

Claims (1)

[Scope of Claims] A rotor for an axial flow fluid machine, in which each rotor has a wing portion, a root portion, and a portion below the root portion, in order to convert the energy of a power fluid flowing in the axial direction into a U rotation of the rotor. a plurality of rotor blades having a guide device for guiding cooling loss from the blades through the airfoil and into a power fluid discharge passage surrounding the wing; A rotor disk having a plurality of indentations around its periphery, the rotor disk having a guiding device for guiding cooling fluid from the rotor into a space at the radially innermost end of each indentation between the root and the rotor disk. It consists of a combination of a rotor disk and a plurality of sealing devices for sealing the downstream end of the space, and the front sealing box is inserted into the cooling style body from the space in front of the guide device in the rotor blade. A rotor for an axial flow fluid machine that does not require any disassembly or structural change of the rotor disk for its assembly.