EP1309773A1

EP1309773A1 - Turbine vane system

Info

Publication number: EP1309773A1
Application number: EP01962905A
Authority: EP
Inventors: Hans-Thomas Bolms; Michael Strassberger; Peter Tiemann
Original assignee: Siemens AG
Current assignee: Siemens AG
Priority date: 2000-08-16
Filing date: 2001-08-03
Publication date: 2003-05-14
Anticipated expiration: 2021-08-03
Also published as: EP1309773B1; ES2255567T3; US20030180147A1; WO2002014654A1; EP1180578A1; US7201564B2; JP2004506827A; JP4726389B2; DE50108476D1

Abstract

The invention relates to a turbine vane (1), especially a turbine vane of the last stages, respectively comprising a lower area (2) which is radially and externally arranged, an upper area (3) which is radially and internally arranged, and a radial cooling air channel (4) extending between the upper area and the lower area. Cooling air (23) can be introduced into said channel via an inlet (36) in the lower area, and can be at least partially discharged via an outlet (35) in the upper area. The cooling air channel comprises a radial inner channel through which the cooling air flows from the lower area to the upper area, and an outer channel (9) which is adjacent to the inner channel and which at least partially surrounds the inner channel on the circumferential side thereof. Said outer channel communicates with the inner channel and comprises an outlet (12) which is arranged in the lower area. Part of the cooling air (41) flows back in the direction of the lower area via the outer channel and emerges via the outlet.

Description

description

Arrangement of turbine guide

The invention relates to an arrangement of turbine guide vanes, in particular turbine guide vanes of the rearmost stages, each having a radially outer foot region, a radially inner head region and a radial cooling air duct running between the head region and foot region, can be introduced into the cooling air into an inlet opening in the foot region and through an outlet opening in the head area can be at least partially led out.

A hot gas stream driving a turbine is conducted from the stationary turbine guide vanes to the turbine rotor blades, which are fastened on disks rotating about a central turbine axis. A circular arrangement of turbine guide vanes, which are fastened with their radially outer base regions to a stationary turbine housing wall, alternates with an arrangement of turbine rotor blades on a rotating disk. The radially inner head regions of the turbine guide vanes adjoin a U-shaped inner ring which has a labyrinth seal on its outside, which seals against the flow of hot gas around the U-ring.

Cooling air is generally used to cool the turbine blades heated by the hot gas flowing past. In the case of turbine guide vanes, the cooling air flows, for example, through a radial cooling air duct arranged in the turbine guide vane, from the radially outer root region of the turbine guide vane to the radially inner head region / the cooling air is introduced from the head region into the adjacent U-shaped ring. This is cooled by the cooling air flowing past. An overpressure of the cooling air is also intended to prevent hot gas from entering the area of the head cυ K 1V> F ¹ F »

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Flows back foot area and flows out through the outlet opening.

The division of the cooling air duct into the inner and outer duct ensures that the cooling air first flows through the inner duct, and flows out at the foot region partly for cooling the U-shaped ring and partly flows back again after being diverted through the outer duct. The total amount of cooling air flows through the inner duct and a smaller amount of cooling air flows around it in the form of a counterflow. The cooling air flow in the outer duct surrounding the inner duct is very fast. It therefore provides good cooling of the surrounding areas of the turbine guide vane due to the increased cooling capacity of a fast cooling air flow. The cooling air flowing back in a rapid flow isolates the inner channel on the one hand and enables the cooling air at the outflow point into the U-ring at the head region to have a low temperature without large amounts of cooling air having to be used. At the same time, the cooling air flowing back cools the side walls of the cooling air duct and thus the surrounding areas of the turbine guide vane, which are the load-bearing areas of the turbine guide vane. According to the invention, the walls of the turbine blade, which surround the cooling air duct, are thicker than in the prior art and thus more stable. By redirecting part of the cooling air flow through the outer duct and the faster ducting of the cooling air in the outer duct, the total quantity of cooling air is thus reduced and at the same time the temperature of the cooling air emerging from the turbine guide vane for cooling the U-ring is reduced. The invention thus offers the advantage that both the turbine guide vane and the U-shaped ring are sufficiently cooled with small amounts of cooling air.

If the turbine guide vanes are turbine guide vanes of the rearmost stages, there is a relatively large saving compared to the use of conventional cooling air ducts 00 cυ tt F ¹ F ¹

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crowd out. The cooling of the turbine guide vane is sufficient at the relatively low temperatures, especially in the rear stages.

An exemplary embodiment of the invention is to be given on the basis of the figures. Show it:

1 is a turbine guide vane of the rearmost stages,

Fig. 2 shows a longitudinal section through a turbine guide vane according to Fig.l and

3 shows a schematic representation of the temperature development of the cooling air mass flows.

Fig. 1 shows a perspective view of a turbine guide vane 1 of the rearmost stages. With the help of the foot region 2, which has holding projections 24, the turbine guide vane 1 is fastened to an inner wall, not shown, of a cylindrical turbine housing. From there, the turbine guide vane 1 extends with its blade 18 radially in the direction of a central turbine axis 30 of the turbine housing. The radially inner end of the turbine guide vane 1 is formed by the head region 3, which has a plateau 25 and an arcuate recess 26 which is radially inner with respect to the turbine axis 30. A U-shaped ring 19 is coupled to this head region 3 by means of rail-like holding projections 27. The holding projections 27 engage in holding grooves 28 of the U-shaped ring 19. The arcuate recess 26 of the head region 3, together with the U-shaped ring 19, delimits a cavity 20, the longitudinal direction 29 of which extends transversely to the turbine axis 30 and to a blade axis 31. A labyrinth seal 21 is located radially on the inside of the U-shaped ring 19. This seals the turbine rotor blade disk 22, which is located underneath and rotates around the central turbine axis 31 when the turbine is in operation Turbine blades, not shown, is occupied, against a direct flow of hot gas 17.

The airfoil 18 has a radial, cylindrical cooling air channel 4 which runs continuously from an inlet opening 36 of the cooling air 23 in the foot region 2 of the turbine guide vane 1 to its outlet opening 35 of the cooling air in the head region 3 of the turbine guide vane 1. It has a cross-sectional contour 34 which in the area of the airfoil 18 and the foot area 2 is similar to the outer contour 16 of the airfoil 18. When viewed from the foot area 2 to in front of the head area 3, the shape of the cross-sectional contour 34 of the cooling air duct 4 remains essentially the same, but may decrease in size. When the cooling air duct 4 enters the head region 3, the cross section 34 in narrows

Form of a circumferential step 33. This narrowed cross section 34 is then approximately maintained up to the recess 26 in the head region 3, in which the outlet opening 35 of the cooling channel 4 lies in the cavity 20. A cylindrical cooling air guide tube 13 is inserted approximately centrally in the cooling air duct 4. The cooling air guide tube 13 has an almost constant elliptical cross section 15. The cooling air guide tube 13 is held at the head region 3 of the turbine guide vane 1 essentially in that it extends to the circumferential step 33 with a cross section 15 adapted to the transition, or is even inserted into the narrowed cross section 34 of the cooling air duct 4 in the head region 3. In the foot region 2, the cooling air guide tube 13 is held in the center, for example, by spacing webs 37 attached to side walls 8 of the cooling air duct 4. The cooling air duct 4 can be cast directly during the casting of the turbine blade 1 by inserting a casting core. The cooling air guide tube 13 is inserted into the cooling air duct 4 after the casting.

In the foot area 2, the cooling air 23 is introduced into the inlet opening 36 of the cooling air guide tube 13, which extends to an upper side 32 of the foot area 2 of the turbine guide vane 1. Cυ cυ t 10 F ^» F ¹

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Flow in the longitudinal direction 31 up to an end length 1 of the cooling air duct 4. The maximum temperature Tmax is not reached by the continuous current 42, as a result of which the U-shaped ring can be cooled sufficiently. The other cooling air portion 41, however, takes the greater part of the heat and transports it out of the turbine blade without the heat being able to damage the temperature-sensitive areas. The total amount of cooling air 23, the sum of the two power components 41, 42 is significantly lower than in the prior art.

Claims

claims

1. turbine guide vane (1), in particular turbine guide vane (1) of the rearmost stages, each with a radially outer foot region (2), a radially inner head region (3) and a radial cooling air duct running between the head region (3) and the foot region (2) (4), can be introduced into the cooling air (23) into an inlet opening (36) in the foot region (2) and can be at least partially discharged through an outlet opening (35) in the head region (3), characterized in that the cooling air duct (4) has a radial inner duct through which the cooling air (23) flows from the foot region (2) to the head region (3) and an outer duct (9) adjoining the inner duct, which at least partially surrounds the inner duct on the circumference, which communicates with the inner duct and which has an outlet opening (12 ) in the foot area (2), a cooling air portion (41) flowing back in the direction of the foot area (2) through the outer channel (9) and through the outlet out opening (12).

2. Turbine guide vane according to claim 1, so that the outer channel (9) practically completely surrounds the inner channel on the circumferential side.

3. Turbine guide vane according to claim 1 or 2, so that the inner duct has at least one communication bore (10) through which the cooling air portion (41) can pass into the outer duct (9).

4. Turbine guide vane according to claim 3, characterized in that the communication bore (10) is arranged in an end region (6) on the head side.

5. Turbine guide vane according to one of claims 1 to 4, so that the turbine guide vane (1) has an outlet opening (12) in the foot region (2) in a trailing edge region (11), which communicates with the outer channel (9).

6. Turbine guide vane according to one of claims 1 to 5, d a d u r c h g e k e n n z e i c h n e t that the inner channel is cylindrical.

7. Turbine guide vane according to one of claims 1 to 6, characterized in that the inner channel is a cooling air guide tube (13) which can be inserted into the cooling air channel (4) and which is at a distance (14) from the inner wall (8) of the cooling air channel (4). is arranged and the

Outer duct (9) is formed by the space between the cooling air guide tube (13) and the inner wall (8) of the cooling air duct (4).

8. Turbine guide vane according to claim 7, characterized in that the distance (14) is less than a cross section (15 ^" ) of the cooling air guide tube (13).

9. turbine guide vane according to one of claims 1 to 8, d a d u r c h g e k e n n z e i c h n e t that the flow of the cooling air portion (41) in the outer channel (9) is faster than in the inner channel.

10. Casting method for producing a turbine guide vane, in particular a turbine guide vane according to one of claims 1 to 9, in which the cooling air duct (4) of the turbine guide vane (1) is produced by a core, characterized in that the core has a smaller cross section than usual Cores for the casting of turbine guide vanes, after the casting into the cooling air duct (4) with at least one communication hole (10) Provided cooling air guide tube (13) at a distance (14) to the inner walls (8) of the cooling air duct (4), and in the inner walls (8) in the trailing edge area (11) of the foot area (2) of the turbine guide vane (1) up to the outer contour (16) of the turbine guide vane (1) through outlet openings (12) are introduced.