Patent Application
20180017067
Gas turbine engines, such as those which power aircraft and industrial equipment, employ a compressor to compress air that is drawn into the engine and a turbine to capture energy associated with the combustion of a fuel-air mixture. Clearances that are maintained between, e.g., rotating and static structure in the engine impact the performance and reliability of the engine. For example, in connection with the compressor, if the (radial) clearance between a blade tip and an engine case is too large there will be a loss of output performance/efficiency. On the other hand, if the clearance between the blade tip and the engine case is too small then the blade tip may rub against the engine case (or a seal disposed between the blade tip and the engine case), which may cause the components to wear over time.
The clearance is a function of various parameters. For example, materials that are used in the construction of a component impact the rate of thermal growth/expansion of that component. Components that are closer to the engine centerline tend to be exposed to elevated temperatures relative to those components located further outward or radially distant from the centerline and hence tend to experience greater degrees of growth/deflection for a given material. Still further, the operative state of the engine (or the associated aircraft, where applicable) may impact the loads that a given component experiences at a given point in time; for example, an increase in load may be experienced by a component during acceleration relative to a steady state operation.
In short, what is needed are techniques to control the degree of growth/expansion of a component under various loads (e.g., thermal loads) in order to be able to tailor a profile of a clearance over various operative states of an engine.
The following presents a simplified summary in order to provide a basic understanding of some aspects of the disclosure. The summary is not an extensive overview of the disclosure. It is neither intended to identify key or critical elements of the disclosure nor to delineate the scope of the disclosure. The following summary merely presents some concepts of the disclosure in a simplified form as a prelude to the description below.
Aspects of the disclosure are directed to a system of an engine, comprising: a clearance control thermal ring, and a seal ring, where a radial gap with respect to an axial centerline of the engine is formed between a radial end of the clearance control thermal ring and a facing radial surface of the seal ring, where the clearance control thermal ring is made of a first material and the seal ring is made of a second material that is different from the first material, and where a first coefficient of thermal expansion of the first material is less than a second coefficient of thermal expansion of the second material. In some embodiments, the clearance control thermal ring and the seal ring define a first radial gap during a first loading condition. In some embodiments, the first loading condition is associated with a steady state operation of the engine. In some embodiments, the radial gap is located radially inward of the clearance control thermal ring. In some embodiments, the radial gap is located radially outward of the seal ring. In some embodiments, the clearance control thermal ring and the seal ring are in contact with one another during a second loading condition. In some embodiments, the second loading condition is associated with acceleration of the engine. In some embodiments, the first material is a first nickel-based alloy and the second material is a second nickel-based alloy. In some embodiments, the first material includes at least one of Haynes® 242 alloy or Incoloy®909 alloy and the second material includes Waspaloy® alloy. In some embodiments, the system further comprises a seal coupled to the clearance control thermal ring. In some embodiments, the seal includes a flange, the system comprising: a bolt and a nut that connect the clearance control thermal ring to the flange. In some embodiments, the clearance control thermal ring includes a slotted hole that seats the bolt. In some embodiments, the system further comprises at least one of a washer or a sleeve disposed between the clearance control thermal ring and a head of the bolt. In some embodiments, the seal is coupled to a stator at an axially forward end of the seal and a guide vane at an axially aft end of the seal. In some embodiments, the clearance control thermal ring includes a first leg and a second leg. In some embodiments, the first leg is substantially oriented in a radial direction and the second leg is substantially oriented in an axial direction. In some embodiments, the clearance control thermal ring is substantially L-shaped.
Aspects of the disclosure are directed to an apparatus comprising: a clearance control thermal ring, a seal ring, and a bolt and a nut that attach the clearance control thermal ring to the seal ring, where the clearance control thermal ring and the seal ring form at least one radial gap with respect to an axial centerline of an engine during a first loading condition, and where the clearance control thermal ring and the seal ring have respective first and second coefficients of thermal expansion that are different from one another such that the at least one radial gap is closed during a second loading condition that is different from the first loading condition. In some embodiments, the at least one radial gap is located radially inward of the clearance control thermal ring.
The present disclosure is illustrated by way of example and not limited in the accompanying figures in which like reference numerals indicate similar elements. The drawings are not necessarily drawn to scale unless specifically indicated otherwise.
It is noted that various connections are set forth between elements in the following description and in the drawings (the contents of which are included in this disclosure by way of reference). It is noted that these connections are general and, unless specified otherwise, may be direct or indirect and that this specification is not intended to be limiting in this respect. A coupling between two or more entities may refer to a direct connection or an indirect connection. An indirect connection may incorporate one or more intervening entities.
In accordance with aspects of the disclosure, apparatuses, systems, and methods are directed to a clearance control thermal ring. The clearance control thermal ring may be coupled to a flange, such as for example a flange of an outer air seal. The clearance control thermal ring may control thermal growth of an aft seal ring. For example, the clearance control thermal ring may limit continued thermal growth of an aft seal ring beyond a threshold, thereby providing for a tailoring in terms of a clearance profile.
Aspects of the disclosure may be applied in connection with a gas turbine engine.
The engine sections 18-21 are arranged sequentially along the centerline 12 within an engine housing 22. Each of the engine sections 18-19B, 21A and 21B includes a respective rotor 24-28. Each of these rotors 24-28 includes a plurality of rotor blades arranged circumferentially around and connected to one or more respective rotor disks. The rotor blades, for example, may be formed integral with or mechanically fastened, welded, brazed, adhered and/or otherwise attached to the respective rotor disk(s).
The fan rotor 24 is connected to a gear train 30, for example, through a fan shaft 32. The gear train 30 and the LPC rotor 25 are connected to and driven by the LPT rotor 28 through a low speed shaft 33. The HPC rotor 26 is connected to and driven by the HPT rotor 27 through a high speed shaft 34. The shafts 32-34 are rotatably supported by a plurality of bearings 36; e.g., rolling element and/or thrust bearings. Each of these bearings 36 is connected to the engine housing 22 by at least one stationary structure such as, for example, an annular support strut.
During operation, air enters the turbine engine 10 through the airflow inlet 14, and is directed through the fan section 18 and into a core gas path 38 and a bypass gas path 40. The air within the core gas path 38 may be referred to as “core air”. The air within the bypass gas path 40 may be referred to as “bypass air”. The core air is directed through the engine sections 19-21, and exits the turbine engine 10 through the airflow exhaust 16 to provide forward engine thrust. Within the combustor section 20, fuel is injected into a combustion chamber 42 and mixed with compressed core air. This fuel-core air mixture is ignited to power the turbine engine 10. The bypass air is directed through the bypass gas path 40 and out of the turbine engine 10 through a bypass nozzle 44 to provide additional forward engine thrust. This additional forward engine thrust may account for a majority (e.g., more than 70 percent) of total engine thrust. Alternatively, at least some of the bypass air may be directed out of the turbine engine 10 through a thrust reverser to provide reverse engine thrust.
Referring to
The system 200 is shown as including structures 202a and 202b. In one exemplary embodiment, the structure 202a may be a fixed structure/stator and the structure 202b may be a guide vane. The axially-oriented gap/cavity 206 between the structures 202a and 202b may accommodate a blade and an associated rotor or an integrally bladed rotor (IBR). An outer air seal 210 may be substantially axially located between the structures 202a and 202b.
The seal 210 (e.g., a flange 212 of the seal 210 that projects radially outward) may be coupled to an aft seal ring 216. The aft seal ring 216 may be radially and/or axially coupled to an inner diffuser case at the aft end via one or more coupling techniques (e.g., interference fit, use of a bolt, etc.). The aft seal ring 216 may be coupled to a clearance control thermal ring (CCTR) 220. A bolt 228 and a nut 234 may be used for coupling (e.g., attaching) the CCTR 220 and the flange 212 to one another as shown in
The CCTR 220 may be composed of two or more legs, such as for example a first leg 220a and a second leg 220b. The first leg 220a may be oriented substantially radially and the second leg 220b may be oriented substantially axially with respect to the axial centerline 12 (
The blade (or the associated rotor) located in, e.g., the gap 206 may tend to grow and contract based on thermal loading over the various operational states of the engine. To accommodate the radially outward growth, it may be desirable for the aft seal ring 216 to grow radially outward as well to prevent/minimize/reduce rubbing/wear between the blade and the seal 210. On the other hand, if an excessive amount/degree of growth is experienced by the aft seal ring 216 then an excessively large radial gap may be formed between the blade and the seal 210, which may result in a loss of engine efficiency/performance. Thus, if the growth of the blade/rotor can be substantially matched to the effective growth of the aft seal ring 216 then a compromise can be made between potential wear on the one hand and performance on the other hand.
Referring to
While
The rate at which the gap 504 (or the gap 240) decreases under thermal loading may be based on the materials that are used in the construction of one or more of the aft seal ring 216, the CCTR 220, the bolt 228, and the nut 234. For example, the CCTR 220 may be made of a material that has a coefficient of thermal expansion that is less than a coefficient of thermal expansion associated with the aft seal ring 216. In an exemplary embodiment, the aft seal ring 216 may be made of a first nickel-based alloy, such as Waspaloy® alloy, whereas the CCTR 220 may be made of a second nickel-based alloy, such as Haynes® 242 alloy or Incoloy® 909 alloy.
Referring to
Technical effects and benefits of this disclosure include a sealing arrangement that maintains a target tolerance in terms of clearance between rotating and stationary hardware. The use of a CCTR may limit an extent to which a seal ring is allowed to grow to maintain such a target clearance.
Aspects of the disclosure have been described in terms of illustrative embodiments thereof. Numerous other embodiments, modifications, and variations within the scope and spirit of the appended claims will occur to persons of ordinary skill in the art from a review of this disclosure. For example, one of ordinary skill in the art will appreciate that the steps described in conjunction with the illustrative figures may be performed in other than the recited order, and that one or more steps illustrated may be optional in accordance with aspects of the disclosure. One or more features described in connection with a first embodiment may be combined with one or more features of one or more additional embodiments.
