GB2444653A

GB2444653A - Vorticity control in a gas turbine engine

Info

Publication number: GB2444653A
Application number: GB0800937A
Authority: GB
Inventors: David Macmanus
Original assignee: Rolls Royce PLC
Current assignee: Rolls Royce PLC
Priority date: 2003-11-13
Filing date: 2003-11-13
Publication date: 2008-06-11
Anticipated expiration: 2023-11-13
Also published as: GB0800937D0; GB2444653B

Abstract

An arrangement or method for reducing vorticity downstream of a component in the gas flow of a gas turbine engine, such as a turbine nozzle guide vane, involves means for introducing a gas into the gas flow in a direction or directions to counteract wake vorticity produced downstream of the component. Cooling air may be directed through a guide vane and out through trailing edge outlets in directions to counteract vorticity produced downstream of the guide vane. The outlets may be arranged to direct flow upwardly from two upper outlets and downwardly from two lower outlets, upwardly from outlets on the vane suction side and downwardly from outlets on the vane pressure side, or in a counteracting vortices generated by helical fences, rifling, groves or vanes within passages leading to the outlet.

Description

Vorticity Control in a Gas Turbine Engine This invention relates to an

arrangement for reducing vorticity in a gas turbine engine, a component for a gas turbine engine, and a turbine for a gas turbine engine.

In gas turbine engines a wake is produced downstream of components past which gases flow, and especially components which turn the direction of the gas flow. This wake may roll up into a discrete vortex of intense vorticity that can result in significant flow distortions as well as mixing and interference losses downstream thereof. Such components include turbine aerofoils, and the wake produced downstream thereof can have an effect upon subsequent blade rows where it results in flow distortions, incidence and other loss mechanisms.

According to the present invention there is provided an arrangement for reducing vorticity downstream of a component in a gas flow of a gas turbine engine, the arrangement including means for introducing a gas into the gas flow in a direction or directions to counteract the wake vorticity produced downstream of the component wherein means are provided for introducing gas through the component.

The arrangement may be configured such that the introduced gas is air, and may be cooling air which has already passed through the component.

Guide means may be provided which are arranged to direct the introduced gas at an inclination relative to the gas flow.

The component may include an aerofoil, which component may form part of a compressor or turbine, and in particular the component may be a turbine nozzle guide vane.

Embodiments of the present invention will now be described by way of example only and with reference to the accompanying drawings, in which:-Fig. 1 is a diagrammatic cross sectional view through a conventional turbine nozzle guide vane of a gas turbine engine; Fig. 2 is a diagrammatic axial section view through part of a conventional turbine looking upstream; Fig. 3 is a similar view to Fig. 2 but with other indications provided; Fig. 4 is a diagrammatic axial section view through part of a first gas turbine according to the invention looking upstream; Fig. 5 is a similar view to Fig. 4 of a second gas turbine according to the invention; Fig. 6 is a similar view to Fig. 5 but with other markings thereon; Fig. 7 is a diagrammatic cross sectional view through part of a component of the second gas turbine; Fig. 8 is a similar view to Fig. 1 but of a turbine nozzle guide vane according to a third embodiment of the invention; and Figs. 9 and 10 are respectively views in the direction of the lines A-A and B-B illustrated in Fig. 8.

Fig. 1 shows a conventional turbine nozzle guide vane with a leading edge 12 and a trailing edge 14. The inlet gas flow direction is shown by the arrow 16 and this gas flow is turned by the guide vane 10 to the direction shown by the arrows 18. The shape of the guide vane 10 produces a pressure side 20 and a suction side 22. As is conventional air cooling is provided through the nozzle guide vane 10 as illustrated by the arrows 24, and some cooling air may exit the guide vane 10 at the trailing edge 14.

Figs. 2 and 3 diagrammatically show two such nozzle guide vanes 10 looking upstream with their suction sides 22 and pressure sides 20. Arrows 26 in Fig. 2 illustrate how the gas flow may tend to pitch down on the suction side 22 whilst pitching up on the pressure side 20. Fig. 3 indicates by arrows 28 an example of the induced negative streamwise vorticity. In Figs. 2 and 3 the guide vanes 10 are seen extending between the casing 30 and the hub 32.

Fig. 4 shows a first arrangement according to the invention with a nozzle guide vane 34 extending between the casing 30 and hub 32. Again the view is upstream so the trailing edge 36 is visible with the pressure side 20 and suction side 22. Arrows 38 illustrate the main flow pitching down on the suction side 22 and pitching up on the pressure side 20. The trailing edge 36 is shown schematically to have four outlets 40 for cooling air passing through the nozzle guide vane 34. The lower two outlets 42 are directed downwardly as shown by the arrows illustrated therein whilst the upper two outlets 44 are directed upwardly again as illustrated by the arrows shown therein. The inclination and arrangement of the outlets 40 is chosen to, result in reduced streamwise vorticity in the wake of the guide vane 34.

Figs. 5 and 6 show a second embodiment with a turbine nozzle guide vane 46 again extending between the casing 30 and hub 32. In this instance seven outlets 48 are schematically shown. Four upwardly inclined outlets 50 are provided on the suction side 22, whilst three offset downwardly inclined outlets 52 are provided on the pressure side 20. Fig. 6 illustrates the main stream induced negative vorticity by the arrow 54, whilst the arrow 56 illustrates the positive vorticity induced by the cooling air through the outlets 48.

Whilst in this example the outlets 50 and 52 are offset, it is not always necessary to provide an offset configuration.

Fig. 7 illustrates the trailing edge 58 of the nozzle guide vane 46. Coolant supply chambers 59, which may he shared or separate, for the cooling air passing through the nozzle guide vane 46 are shown leading to outlets 50, 52, with the outlets 50 angled down and the outlets 52 angled up. The freestrearn flow pitching up is shown by the arrow 60 on the pressure side 20, with the freestream flow pitching down illustrated by the arrow 62 on the suction side 22. The flow of cooling air is illustrated by the arrows 64.

Figs. 8 to 10 illusLrate a urther turbine nozzle guide vane 66 which again ejects cooling air through its trailing edge 68. A plurality of passages 70 are provided in the trailing edge 68 for ejection of cooling air. Helical fences /2 are provided in the passages 70 to swirl cooling air passing therethrough as illustrated by the arrows 74 which show a positive induced vorticity to counteract the main flow pitching down on the suction side 22 and pitching up on the pressure side 20. Whilst helical fences 72 have been described, the swirling of the cooling air can he produced by a number of other means such as rifling, grooves or vanes.

There are thus described various arrangements for counteracting the wake vorticity produced behind turbine nozzle guide vanes. The reduction of this vorticity provides for a number of advantages. These include increased performance, due to the reduction of efficiency losses such as mixing, flow distortions and downstream incidence effects. In addition, aerodynamic unsteady forcing contributing to fatigue failure of downstream components is also reduced.

Various other modifications may be made without departing from the scope of the invention. For instance, the ejection of the cooling air could be in a number of different directions, and could extend at least to some degree laterally to counteract the vorticity. Obviously any required combination of inclinations and number of cooling air ejectors can be chosen. These ejectors can be nozzles or could for example be openings directed onto a profiled member. Whilst the use of cooling air has only been described, it may be possible for air other than cooling air or other gases to be used to counteract the vorticity. This would obviously be of particular relevance to uncooled components.

Whilst the invention has been described in terms o nozzle guide vanes for turbines, the invention could be applicable to a wide range of products located in the gas stream, and particularly products which turn the gas stream.

Such products include for instance compressor guide vanes.

Whilst endeavouring in the foregoing specification to draw attention to those features of the invention believed to be of particular importance it should be understood that the Applicant claims protection in respect of any patentable feature or combination of features hereinbefore referred to and/or shown in the drawings whether or not particular emphasis has been placed thereon.

Claims

1. An arrangement for reducing vorticity downstream of a component (34,46,66) in the gas flow of a gas turbine engine, characterised in that the arrangement includes means (40,42,44,48,50,52,70) for introducing a gas into the gas flow in a direction or directions to counteract the wake vorticity produced downstream of the component (34,46,66).

2. An arrangement according to claim 1, characterised in that means (40,42,44,48,50,52,70) are provided for introducing the introduced gas through the component (34,46,66).

3. An arrangement according to claim 2, characterised in that the arrangement is configured such that the introduced gas is air, and may be cooling air which has already passed through the component (34,46,66).

4. A gas turbine engine provided with an aerofoil as claimed in any one preceding claim. I.

S **** a a... * a * S I S.

4. An arrangement according to any of the preceding claims, characterised in that guide means (40,42,44,48,50,52,70) are provided which are arranged to direct the introduced gas at an inclination relative to the gas flow.

5. An arrangement according to claim 4, characterised in that the guide means may include slots or openings (40,42,44,48,50,52,70), and openings may be directed onto guide formations to provide the required inclination.

6. An arrangement according to claims 4 or 5, characterised in that the guide means (40,42,44,48,50,52,70) are arranged to directly introduce gas in different directions from different parts of the component (34,46,66), and the guide means (40,42,44,48,50,52,70) may be arranged to direct the introduced gas in different directions from different sides of the component (34,46,66).

7. An arrangement according to any of claims 4 to 6, characterised in that the guide means (74) are arranged to swirl the introduced gas in a manner which results in vorticity with an opposite sign to that of the wake vorticity, and the guide means may include passages with vanes, grooves, fences (72), rifling or other formations on the walls thereof to cause swirling.

8. An arrangement according to any of the preceding claims, characterised in that the component (34,46,66) includes an aerofoil, which component may form part of a compressor or turbine, and in particular the component may be a turbine nozzle guide vane (34,46,66).

9. A component for a gas turbine engine, characterised in that the component (34,46,66) is according to any of the preceding claims.

10. A component according to claim 9, characterised in that the component is a turbine nozzle guide vane (34,46,66).

11. A turbine for a gas turbine engine characterised in that the turbine includes a plurality of components (34,46,66) according to any of the preceding claims.

12. A method of reducing wake vorticity downstream of a component in the gas flow in a gas turbine engine characterised in that the method includes introducing a gas in a direction or directions to counteract the wake vorticity produced downstream of a component (34,46,66).

13. A method according to claim 12, characterised in that the gas is introduced through the component (34,46,66).

14. A method according to claim 13, characterised in that the introduced gas is directed in different directions from different parts of the component (34,46,66).

15. A method according to any of claims 12 to 14, characterised in that the introduced gas is swirled to result in a vorticity with an opposite sign to that of the wake vorticity.

16. An arrangement for reducing vorticity downstream of a component in a gas flow of a gas turbine engine, the arrangement being substantially as hereinbefore described and with reference to the accompanying drawings.

17. A component for a gas turbine engine, the component being substantially as hereinbefore described and with reference to the accompanying drawings.

18. A turbine for a gas turbine engine, the turbine being substantially as hereinbefore described and with reference to the accompanying drawings.

19. A method of reducing wake vorticity downstream of a component in the gas flow of a gas turbine engine, the method being substantially as hereinbefore described and with reference to the accompanying drawings.

20. Any novel subject matter or combination including novel subject matter disclosed herein, whether or not within the scope of or relating to the same invention as any of the preceding claims.

* AMENDMENTS TO THE CLAIMS HAVE BEEN FILED AS FOLLOWERS:-

1. A gas turbine engine aerofoil configured to be operationally located in the flow of a gas turbine engine, said aerofoil being arranged to be cooled internally by a flow of cooling air and having a trailing edge provided with a plurality of outlets for the exhaustion therefrom of at least some of said cooling air, some of said outlets being so arranged adjacent the pressure surface of said aerofoil as to exhaust said cooling air therefrom in a generally rrH11v inwRrd direction to interact with said gas turbine engine flow over said pressure surface of said aerofoil and other of said outlets being arranged adjacent the suction surface of said aerofoil to exhaust said cooling air therefrom in a generally radially outward direction to interact with said gas turbine engine flow over said suction surface of said aerofoil 2. A gas turbine engine aerofoil according to claim 1, wherein the aerofoil is a turbine nozzle guide vane.

3. A gas turbine engine aerofoil substantially as ". hereinbefore described and with reference to the * ** accompanying drawings. **