TURBINE BLADE COOLING
A blade includes a root and an elongate portion extending to a tip, the elongate portion having an aerofoil-shaped cross-section. The aerofoil has leading and trailing edges, and suction and pressure sides. The tip includes a squealer defining a gutter at the tip, the squealer extending from the trailing edge along the entirety of a first of the suction and pressure sides, around the leading edge and partly along a second of the suction and pressure sides leaving a gap between the trailing edge and an end of the wall. A main trailing edge cooling channel extends within the elongate portion in a direction from root to tip adjacent the trailing edge and exits into the gutter. The main trailing edge cooling channel includes a bend just downstream of the exit, the exit displaced from a camber line of the blade elongated portion towards the second side.
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The present disclosure relates to shroudless turbine blades having squealer tips. More particularly the invention relates to the arrangement of internal cooling channels in this region of the blade and the geometry of squealer tips which accommodate the cooling channels.
BACKGROUNDIn a gas turbine engine, a compressor is arranged to compress air for delivery to a combustor. The combustor mixes the compressed air with fuel and ignites the mixture. Gas products of this combustion are directed at a turbine blade assembly causing rotation of the blades and the production of power from the turbine assembly. Combustion temperatures may exceed 1400° C. and typical configurations expose the turbine blade assemblies to these high temperatures. Turbine blades are made of materials capable of withstanding such high temperatures and often contain cooling systems for prolonging the life of the blades, reducing the likelihood of failure as a result of exposure to these excessive temperatures.
A turbine blade has a root portion at one end and an elongated portion of aerofoil shaped cross section extending from the root portion. In a turbine blade assembly, the root portion is coupled to a platform, typically a radially outer surface of a circumferential wall of a rotor disc. The elongated portion extends radially outwardly and terminates in a tip. The aerofoil shaped cross section has a leading edge and a trailing edge joined by a suction side and a pressure side.
Efforts are continually being made to improve efficiency in gas turbine engines. It is known that a significant factor in reducing efficiency of the turbine assembly is attributable to the leakage of the combustion gas products over the tips of the turbine blades through a small gap between the tips of the blade assembly and a surrounding circumferential housing. It is believed such losses could account for 30% or more of total losses in the turbine assembly. As well as reduced efficiency, consequences include reduced life of turbine components due to high thermal stresses in this region.
It is known to provide turbine blade tips with seals to reduce this gap. Such tip seals are referred to as squealer tips and these are typically machined into a cast turbine blade. A squealer tip is formed as a wall extending around a substantial portion of the aerofoil at the blade tip defining a gutter within. Cooling air which has passed through the elongate portion of the blade may be expelled into this gutter and dispersed into the main gas stream.
For aerodynamic efficiency, it is desirable to minimise the thickness of a blade at its trailing edge. However, thinner sections of blade are more susceptible to the extreme temperatures and are at risk of deformation and damage a consequence of which may be reduced engine efficiency and potential failure of the component. Thus, the trailing edge of the blade must be well cooled.
In known blades having squealer tips, a main trailing edge cooling channel is provided in the elongated portion of the blade and extends from root to tip of the blade. Multiple smaller diameter cooling channels (typically including effusion cooling channels) extend from the main trailing edge channel through the squealer wall in the region of the trailing edge and through the elongate portion to the thinnest parts of the trailing edge. Typically a gallery channel is provided just beneath the gutter surface of the squealer and extends from the main trailing edge cooling channel towards an apogee of the trailing edge. Effusion cooling channels extend through the squealer wall to the gallery channel. The main trailing edge cooling channel is typically integrally cast into the blade. The gallery channel and effusion cooling channels may be added in a subsequent machining step. The gallery channel is typically machined from the apogee of the trailing edge and its end at the apogee subsequently plugged or welded closed to encourage maximum flow to the effusion cooling channels.
An example of a prior art arrangement is shown in
The large overhang 12 of the squealer results in a larger wetted area and hence increased heat flux into the tip during engine operation. This increases the cooling requirement for this region. Other disadvantages of the arrangement include sub-optimal aerodynamic performance at the trailing edge resulting in efficiency losses and a weight penalty.
The present disclosure seeks to provide an improved cooling arrangement and associated squealer tip design which contributes to the mitigation of the problems identified above.
SUMMARYIn accordance with the present disclosure there is provided a blade comprising a root portion and an elongate portion extending from the root portion to a tip, the elongate portion having an aerofoil-shaped cross section having a leading edge, a trailing edge, a suction side and pressure side, the tip including a squealer defining a gutter at the tip wherein the squealer comprises a wall extending from the trailing edge along the entirety of a first of the suction side and pressure side, around the leading edge and partly along a second of the suction side and pressure side leaving a gap between the trailing edge and an end of the wall on the second side, a main trailing edge cooling channel extending within the elongate portion in a direction from root to tip adjacent the trailing edge and exiting into the gutter, wherein the main trailing edge cooling channel includes a bend just upstream of the exit such that the exit is displaced from a camber line of the blade elongated portion towards the gap on the second side.
In some embodiments the first side is the pressure side. In other embodiments the first side is the suction side. The end of the squealer wall on the second side may be curved.
In some embodiments, the gutter in the region of the trailing edge is inclined from the first side towards the second side whereby to maintain a surface which is substantially orthogonal to the walls of the main trailing edge cooling channel where they meet the gutter surface.
The depth of the squealer wall may vary from a first depth at the leading edge to a second and greater depth at the trailing edge. The width of the squealer wall may reduce from a maximum width at a first end of the squealer wall to a minimum width at a second end of the squealer wall. Optionally, the squealer wall may be locally thinned or thickened to accommodate internal passages within the wall or to satisfy manufacturing requirements.
The squealer wall may include a locally extended portion adjacent the trailing edge on the first side, the extended portion extending in a widthwise direction with respect to the squealer wall and away from the gutter. The extended portion may accommodate a gallery channel and associated effusion cooling channels for cooling the trailing edge at the tip.
The gutter may be shallower adjacent the leading edge than it is at the trailing edge. Variation in gutter depth may be achieved by providing an inclined surface to the tip within the gutter. Alternatively, variation in gutter depth is achieved by varying the height of the wall of the squealer between the trailing edge and the leading edge. Gutter depth may vary gradually along an incline, alternatively or in addition, gutter depth may vary due to one or more steps within the gutter. The gallery channel may be shaped to follow variations in the depth of the gutter. For example, the gallery channel may include a stepped section to accommodate a step in the gutter.
A gallery channel may be integrally cast into the blade using an adapted core which defines both the main trailing edge cooling channel and has an extension defining the gallery channel.
The gallery channel may be provided in a shape which minimises flow restriction in the gallery channel. For example the gallery channel is conically tapered from its open end to its closed end. In more complex embodiments, the cross sectional shape of the gallery channel may be varied in a manner designed to tune coolant flow to suit cooling requirements in different regions of the blade tip and squealer. For example, the gallery channel is shaped to encourage optimum flow rates to the film cooling holes in accordance with cooling requirements at the exits of the film cooling holes. For example, to control the impact of aerodynamics in a known operational environment in which the blade is to be used, the gallery may be configured to bias cooling towards one of the suction side and pressure side.
The film cooling channels may comprise effusion cooling channels. Axes of the effusion cooling channels may be inclined to a surface of the squealer wall. The effusion cooling channels may have a varying cross section, for example the effusion cooling channels may include a fanned portion adjacent the exit to a squealer wall surface. Film cooling channels may be introduced after a blade has been cast. For example, the film cooling channels may be drilled using an EDM process.
The blade may be configured for use in a gas turbine engine, for example the blade may be configured for use in a compressor section or turbine section of a gas turbine engine. One useful application of the design of the invention is in blades of a high pressure turbine stage in a gas turbine engine.
For the purposes of exemplification, some embodiments of the invention will now be described with reference to the accompanying Figures in which;
The wall 56 defines a gutter 57 in the tip. As can be seen a plurality of cooling channels 58a, 58b, 58c, 58d, 58e exit the elongate portion of the blade in the gutter 57. Exits to cooling channels 58b, 58c, 58d and 58e sit along a camber line C-C of the blade. Cooling channel 58a is the main trailing edge cooling channel which includes the inclined portion as discussed in accordance with the invention. As can be seen, this channel 58a has an exit which is positioned towards the suction side 51 of the camber line C-C. In a subsequent manufacturing step, the cooling channels 58a, 58b, 58c, 58d and 58e may be blocked at the blade tip by weld caps, each weld cap having a small diameter hole through it (typically 0.5 mm) to allow egress of dust from the internal passages. Film cooling channels may be provided through the suction side and/or pressure side walls to connect with the channels. Capping at the tip encourages greater flow to these film cooling channels.
The gutter 57 includes a step 59 which results in the gutter 57 being deeper towards the trailing edge 54 end of the gutter than the leading edge 53 end of the gutter 57 and also provides an incline from the suction side towards the pressure side. This incline is selected to ensure that the surface of the gutter 57 around the exit of channel 58a is approximately orthogonal to walls of the channel 58a at the exit.
The second end 56b of the squealer wall 56 is gently curved to discourage turbulent flow of cooling air which exits into the gutter 57 from the channels 58a-58e and flows towards the trailing edge 54 to join a main flow of hot air delivered from the combustor to generate work from a turbine assembly of which the blade forms a part.
In the embodiment of
With reference to
The gas turbine engine 600 works in the conventional manner so that air entering the intake 612 is accelerated by the fan 613 to produce two air flows: a first air flow into the high-pressure compressor 614 and a second air flow which passes through a bypass duct 621 to provide propulsive thrust. The high-pressure compressor 614 compresses the air flow directed into it before delivering that air to the combustion equipment 615.
In the combustion equipment 615 the air flow is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high and low-pressure turbines 616, 617 before being exhausted through the nozzle 618 to provide additional propulsive thrust. The high 616 and low 617 pressure turbines drive respectively the high pressure compressor 614 and the fan 613, each by suitable interconnecting shaft.
For example the blades of the high and low pressure turbines 616, 617 may be configured in accordance with blades of the invention described herein.
Other gas turbine engines to which the present disclosure may be applied may have alternative configurations. By way of example such engines may have an alternative number of interconnecting shafts (e.g. three) and/or an alternative number of compressors and/or turbines. Further the engine may comprise a gearbox provided in the drive train from a turbine to a compressor and/or fan.
It will be understood that the invention is not limited to the embodiments above-described and various modifications and improvements can be made without departing from the concepts described herein and claimed in the appended claims. Except where mutually exclusive, any of the features may be employed separately or in combination with any other features and the disclosure extends to and includes all combinations and sub-combinations of one or more features described herein.
Claims
1. A blade comprising a root portion and an elongate portion extending from the root portion to a tip, the elongate portion having an aerofoil-shaped cross section having a leading edge, a trailing edge, a suction side and a pressure side, the tip including a squealer defining a gutter at the tip wherein the squealer comprises a wall extending from the trailing edge along the entirety of a first of the suction side and pressure side, around the leading edge and partly along a second of the suction side and pressure side leaving a gap between the trailing edge and an end of the wall on the second side, a main trailing edge cooling channel extending within the elongate portion in a direction from root to tip adjacent the trailing edge and exiting into the gutter, wherein the main trailing edge cooling channel includes a bend just upstream of the exit such that the exit is displaced from a camber line of the blade elongated portion towards the second side.
2. A blade as claimed in claim 1 wherein the first side is the pressure side and the main trailing edge cooling channel bends towards the suction side.
3. A blade as claimed in claim 1 wherein the first side is the suction side and the main trailing edge cooling channel bends towards the pressure side.
4. A blade as claimed in claim 1 wherein the gutter is shallower adjacent the leading edge than it is at the trailing edge.
5. A blade as claimed in claim 1 wherein the gutter in the region of the trailing edge is inclined from the first side towards the second side whereby to maintain a surface which is substantially orthogonal to the walls of the main trailing edge cooling channel where they meet the gutter.
6. A blade as claimed in claim 1 further comprising a gallery channel integrally cast into the blade using an adapted core which defines both the main trailing edge cooling channel and has an extension defining the gallery channel.
7. A blade as claimed in claim 5 wherein the gallery channel is provided in a shape which minimises flow restriction in the gallery channel.
8. A blade as claimed claim 5 wherein the gallery channel is spout shaped having a larger diameter at an open end where it intersects the main trailing edge cooling channel and a smaller diameter at a closed end which sits just behind an apogee of the trailing edge.
9. A blade as claimed in claim 5 wherein a tip facing surface of the gallery channel is profiled to complement and extend in parallel with the surface of the gutter in the trailing edge region.
10. A blade as claimed in claim 5 wherein the gallery channel is shaped to follow variations in the depth of the gutter.
11. A blade as claimed in claim 5 further comprising an array of film cooling channels extending from the gallery channel and through the squealer wall.
12. A blade as claimed in claim 1 wherein the depth of the squealer wall varies from a first depth at the leading edge to a second and greater depth at the trailing edge.
13. A blade as claimed in claim 1 wherein the width of the squealer wall is variable.
14. A blade as claimed in claim 13 wherein the width of the squealer wall reduces from a maximum width at a first end of the squealer wall to a minimum width at a second end of the squealer wall.
15. A blade as claimed in claim 1 wherein the squealer wall includes a locally extended portion adjacent the trailing edge on the first side, the extended portion extending in a widthwise direction with respect to the squealer wall and away from the gutter.
16. A blade as claimed in claim 1 configured for use in a gas turbine engine.
Type: Application
Filed: Aug 22, 2017
Publication Date: Mar 15, 2018
Applicant: ROLLS-ROYCE plc (London)
Inventors: Martin MOTTRAM (Bristol), David J. HUNT (Lichfield), Haidong LI (Bristol), Shahrokh SHAHPAR (Derby), Stefano CALONI (Derby)
Application Number: 15/683,339