US3861822A - Duct with vanes having selectively variable pitch - Google Patents

Duct with vanes having selectively variable pitch Download PDF

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US3861822A
US3861822A US446231A US44623174A US3861822A US 3861822 A US3861822 A US 3861822A US 446231 A US446231 A US 446231A US 44623174 A US44623174 A US 44623174A US 3861822 A US3861822 A US 3861822A
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actuation
duct
sector
vanes
segment
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US446231A
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Robert P Wanger
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General Electric Co
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General Electric Co
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps

Definitions

  • inlet guide vanes In order to most efficiently utilize the fan and compressor, the air flow entering the upstream end of each must have a precise axial orientation which orientation is determined by the pitch of the blades comprising the respective first rotor stages.
  • inlet guide vanes In order to provide this precise axial orientation of the incoming air, inlet guide vanes have been used in the prior art. Inlet guide vanes are a series of stationary vanes, spaced circumferentially around an annular duct immediately upstream of the associated rotor (fan or compressor) inlet, which vanes have a precise pitch with respect to the incoming air flow.
  • the engine inlet is not subjected to distortion, but there is advantage in changing the angle of attack of the incoming air with respect to all of the rotor blades in the first rotor stage.
  • actuator 35 will be employed to rotate actuation ring 34, but the individual sector actuation means maintained in fixed position.
  • the motion of ring 34 will be carried equally by lever arms 32 to the sector actuation segments 28. Consequently, all of the stator vanes 22 will be changed in pitch by an equal amount determined by the motion of ring 34. (FIG. 2).
  • each said vane includes a vane lever arm for varying the pitch of said vane in response to arcuate movement of said vane lever arm;

Abstract

A gas turbine has a plurality of variable pitch inlet guide vanes. Each inlet guide vane has a vane lever arm for varying the pitch of the vanes in response to arcuate movement of the vane lever arms. Sector actuation segments interconnect adjacent vane lever arms so that circumferential movement of a sector actuation segment causes arcuate movement of the interconnected vane lever arms. Actuation means cooperates with the sector actuation segments and an actuation ring to selectively move the sector actuation segments circumferentially with respect to the actuation ring. The vanes, then, can be varied in pitch in unison or in individual sectors.

Description

United States Patent [1 1 Wanger Jan. 21, 1975 DUCT WITH VANES HAVING SELECTIVELY VARIABLE PITCH [75] Inventor: Robert P. Wanger, Fairfield, Ohio [73] Assignee: General Electric Company,
Cincinnati, Ohio [22] Filed: Feb. 27, 1974 [21] Appl. No.: 446,231
FOREIGN PATENTS OR APPLICATIONS 608,292 11/1960 Canada 415/162 878,988 10/1961 Great Britain ..4lS/l62 Primary Examiner-Henry F. Raduazo Attorney, Agent, or FirmDerek P. Lawrence; Lee H. Sachs [57] ABSTRACT A gas turbine has a plurality of variable pitch inlet guide vanes. Each inlet guide vane has a vane lever arm for varying the pitch of the vanes in response to arcuate movement of the vane lever arms. Sector actuation segments interconnect adjacent vane lever arms so that circumferential movement of a sector actuation segment causes arcuate movement of the interconnected vane lever arms. Actuation means cooperates with the sector actuation segments and an actuation ring to selectively move the sector actuation segments circumferentially with respect to the actuation ring. The vanes, then, can be varied in pitch in unison or in individual sectors.
9 Claims, 3' Drawing Figures DUCT WITH VANES HAVING SELECTIVELY VARIABLE PITCH BACKGROUND OF THE INVENTION 1. Field of the Invention This invention relates to a duct and more particularly to such a duct having variable pitch vanes therein.
2. Description of the Prior Art In conventional gas turbines, axial flow fans and compressors are used to compress the air entering the gas turbine. Such gas turbines include an inlet which diffuses the incoming air in order to more efficiently utilize the ram effect of the high velocity air moving into the gas turbine. Such diffusion increases the overall pressure ratio of the gas turbine as measured between ambient air pressure and the pressure of the air exiting the downstream end of the compressor.
In order to most efficiently utilize the fan and compressor, the air flow entering the upstream end of each must have a precise axial orientation which orientation is determined by the pitch of the blades comprising the respective first rotor stages. In order to provide this precise axial orientation of the incoming air, inlet guide vanes have been used in the prior art. Inlet guide vanes are a series of stationary vanes, spaced circumferentially around an annular duct immediately upstream of the associated rotor (fan or compressor) inlet, which vanes have a precise pitch with respect to the incoming air flow.
It is known in the prior art that the air flow through the inlet will approach the inlet guide vanes at varying angles of attack depending on many factors of gas turbine operation. In order to overcome the problem of varying angle of attack at different operating conditions, inlet guide vanes whose pitch may be varied have been used.
However, it has been found that, under some circumstances, distortion in the form of axial velocity variations at the upstream end of the inlet result in circumferential variation of the angle of attack of the air flow at or near the inlet to the respective rotor stage. It is clear that the use of inlet guide vanes whose pitch is varied, but all of which have the same pitch at any given time, cannot compensate for this circumferential variation in angle of attack.
The present invention solves this problem through the provision of a duct having vanes in which the pitch of individual groups of vanes, comprising two or three vanes each, can be selectively or uniformly controlled. In order to facilitate the description of this invention, the references which follow pertain only to compressors and the application of this invention thereto, but the concepts are equally applicable to fans.
SUMMARY OF THE INVENTION It is therefore a primary object of this invention to provide an arrangement for selectively varying the pitch of a portion of a plurality of vanes disposed in a duct, while maintaining the capability of varying the pitch of all such vanes in unison.
In accordance with the present invention, a duct has an annular flow passage defined interiorly thereof and comprises an actuation ring which is mounted for circumferential movement relative to the duct. A plurality of variable pitch vanes are disposed in the annular flow passage and each vane includes a vane lever arm which is moved arcuately to vary the pitch of the vanes. A plurality of sector actuation segments are provided, each such segment being mounted to predetermined numbers of adjacent vane lever arms so that the vane lever arms are moved arcuately as the sector actuation segments are moved circumferentially. A plurality of actuation means, which actuation means correspond in number to the number of sector actuation segments. are provided. The actuation means cooperate with the actuating ring and corresponding segments to move the corresponding segment circumferentially relative to the actuation ring. In addition, the actuation means serve to link the segments to the actuation ring so that all the vanes may be varied in pitch in unison by circumferential movement of the actuation ring alone.
DETAILED DESCRIPTION OF THE DRAWINGS A more complete understanding of the invention may be had by reference to the specification when taken in conjunction with the accompanying drawings, wherein:
FIG. 1 represents a gas turbine jet engine incorporating the present invention;
FIG. 2 illustrates a portion of one embodiment of the present invention showing a first actuation mode; and
FIG. 3 is a view similar to FIG. 2 and illustrates a second actuation mode.
DETAILED DESCRIPTION OF THE INVENTION Referring now to FIG. 1, a gas turbine 10 is depicted which includes a compressor 12, a combustor section 14, a turbine 18 and exhaust nozzle 20 in a conventional manner. (As indicated above, the concepts hereof are applicable also to fans in turbofan engines, but for simplicity the present turbojet illustration will suffice.) A duct 21 at the upstream end of compressor 12 incorporates a circumferentially extending set of inlet guide vanes 22 disposed in annular flow passage defined interiorly of duct 21.
Referring now to FIGS. 2 and 3, each inlet guide vane 22 is mounted in the flow passage of the duct 21 for rotation about its axis 24 so that its pitch may be varied. Each vane 22 includes a vane lever arm 26 for varying the pitch of vane 22 in response to arcuate movement of corresponding lever arm 26.
A plurality of sector actuation segments 28 is provided. Each segment 28 interconnects adjacent predetermined numbers, here shown as three (3), of vane lever arms 26. Circumferential movement of a sector actuation segment 28 (as shown by arrow 30) causes arcuate movement of the vane lever arms 26 interconnected therewith and thus varies the pitch of vanes 22. Since a conventional number of vanes 22 is eighteen (18), (only six (6) of which are shown for simplicity), in the application of the present invention to the gas turbine of FIG. 1, there will be a total of six (6) sector actuation segments 28 (only two (2) of which are shown for simplicity). Each sector actuation segment 28 cooperates with a segment lever arm 32. Segment lever arm 32 is shown as extension of one of vane lever arms 26, but those skilled in the art will recognize that a separate lever arm may be secured to the sector actuation segments without departing from the spirit of the invention.
An actuation ring 34 extends circumferentially around duct 21. Duct 21 is circumscribed by the actuation ring when the present invention is used as shown in the presently embodied gas turbine application, but
those skilled in the art will recognize that the actuation ring 34 may extend only partially around the duct 21 without departing from the spirit of the invention. Actuation ring 34 is mounted for circumferential movement relative to duct 21 by a plurality of actuation ring arms 36 which are pivoted to duct 21 and to actuation ring 34. Suitable means, such as hydraulic actuators 35 are provided for moving actuation ring 34 circumferentially relative to duct 21.
A plurality of sector actuation means is provided corresponding in number to the number of segments 28 which are provided, here indicated to be six (6). The sector actuation means move sector actuation segments 28 circumferentially relative to actuation ring 34. Each sector actuation means includes a linear hydraulic actuator 42 having a cylinder 44 and piston 46 movable in cylinder 44. Cylinder 44 is pivotably mounted to actuation ring 34 by pivot 48 and piston 46 has a piston rod 47 which is pivotably mounted to its corresponding segment 28 at sector lever arm 32 by pivot 50.
In operation, with gas turbine 10 mounted to an aircraft for propelling the aircraft, certain flight modes of the aircraft will produce distortion in the form of circumferential variations in the axial velocity of the air entering the inlet. These axial velocity variations around the circumference of the inlet are transformed into angle of attack variations when they reach the upstream end of compressor 12 where inlet guide vanes 22 are located. Since the angle of attack of the air flow reaching the first stage of the compressor 12 can vary circumferentially within annular flow passage 23, it is desired to be able to selectively vary the pitch of inlet guide vanes 22 to correct these circumferential variations of angle of attack. Sector actuation segments 28 and actuation ring 34 may be advantageously positioned circumferentially in order to vary the pitch of inlet guide vanes 22 in groups of three and thus to compensate for these circumferential variations in angle of attack and thereby increase the efficiency of gas turbine 10, as shown in FIG. 3.
In certain other modes of operation, the engine inlet is not subjected to distortion, but there is advantage in changing the angle of attack of the incoming air with respect to all of the rotor blades in the first rotor stage. In this situation, actuator 35 will be employed to rotate actuation ring 34, but the individual sector actuation means maintained in fixed position. As a result, the motion of ring 34 will be carried equally by lever arms 32 to the sector actuation segments 28. Consequently, all of the stator vanes 22 will be changed in pitch by an equal amount determined by the motion of ring 34. (FIG. 2).
Thus, the present invention offers a uniquely effective means for solving the distortion problem, while maintaining the capability of varying the angle of attack of the air flow as a whole.
Although the present invention has been described in connection with ducts used to introduce air flow to the compressor of a gas turbine, it will be clear to those skilled in the art that it is not intended to be restricted to such an application. For example, there may be applications where the relation of sector actuation segments 28 and vane lever arms 26 are more advantageous than that shown herein. In accordance with the requirements of such an application, those skilled in the art will recognize that greater or less selectivity may be obtained by having fewer or more, respectively, vane lever arms 26 interconnected by a single sector actuation segment 28 or that a single sector actuation segment may be interconnected with other than contiguous vane lever arms without departing from the spirit of the invention.
Similar modifications, other than that one specifically pointed out, can be made without departing from the invention, and it is intended by theappended claims to cover all such modifications as fall within the true spirit and scope of the invention.
What is claimed as new and desired to be secured by Letters Patent of the United States is:
l. A duct of the type having an annular flow passage defined interiorly thereof, the duct comprising:
a. an actuation ring mounted for circumferential movement relative to said duct;
b. a plurality of variable pitch vanes disposed in said annular flow passage wherein each said vane includes a vane lever arm for varying the pitch of said vane in response to arcuate movement of said vane lever arm;
c. a plurality of sector actuation segments wherein each said segment is pivotably mounted to predetermined numbers of said vane lever arms for moving said vane lever arms arcuately in response to circumferential movement of said sector actuation segment; and
d. a plurality of actuation means corresponding in number to said plurality of sector actuation segments wherein each said actuation means cooperates with said actuation ring and said corresponding sector actuation segment for moving said corresponding sector actuation segment circumferentially relative to said actuation ring whereby the pitch of said vanes may be selectively varied.
2. The duct recited in claim 1 wherein each said sector actuation segment includes a segment lever arm for moving said segment circumferentially in response to arcuate movement of said segment lever arm.
3. The duct recited in claim 2 wherein each said actuation means comprises a linear hydraulic actuator having a cylinder and a piston movable in said cylinder.
4. The duct recited in claim-3 wherein said cylinder is pivotably mounted to said actuation ring and said piston is pivotably mounted to said corresponding segment lever arm.
5. The duct recited in claim 1 wherein said vane lever arms comprising each said predetermined number are contiguous.
6. The duct recited in claim 5 wherein said plurality of vanes is 18 in number, equally spaced with respect to the circumference of said duct, said plurality of sector actuation segments is six in number, and each said predetermined number of vane lever arms is three.
7. The duct recited in claim 1 wherein said actuation ring circumscribes said duct.
8. The duct recited in claim 7 further comprising a plurality of actuation ring arms for mounting said actuation ring to said duct.
9. The duct recited in claim 1 in combination with a gas turbine of the type having a compressor and inlet guide vanes for directing flow to the compressor, wherein said variable pitch vanes comprise said inlet guide vanes.

Claims (9)

1. A duct of the type having an annular flow passage defined interiorly thereof, the duct comprisIng: a. an actuation ring mounted for circumferential movement relative to said duct; b. a plurality of variable pitch vanes disposed in said annular flow passage wherein each said vane includes a vane lever arm for varying the pitch of said vane in response to arcuate movement of said vane lever arm; c. a plurality of sector actuation segments wherein each said segment is pivotably mounted to predetermined numbers of said vane lever arms for moving said vane lever arms arcuately in response to circumferential movement of said sector actuation segment; and d. a plurality of actuation means corresponding in number to said plurality of sector actuation segments wherein each said actuation means cooperates with said actuation ring and said corresponding sector actuation segment for moving said corresponding sector actuation segment circumferentially relative to said actuation ring whereby the pitch of said vanes may be selectively varied.
2. The duct recited in claim 1 wherein each said sector actuation segment includes a segment lever arm for moving said segment circumferentially in response to arcuate movement of said segment lever arm.
3. The duct recited in claim 2 wherein each said actuation means comprises a linear hydraulic actuator having a cylinder and a piston movable in said cylinder.
4. The duct recited in claim 3 wherein said cylinder is pivotably mounted to said actuation ring and said piston is pivotably mounted to said corresponding segment lever arm.
5. The duct recited in claim 1 wherein said vane lever arms comprising each said predetermined number are contiguous.
6. The duct recited in claim 5 wherein said plurality of vanes is 18 in number, equally spaced with respect to the circumference of said duct, said plurality of sector actuation segments is six in number, and each said predetermined number of vane lever arms is three.
7. The duct recited in claim 1 wherein said actuation ring circumscribes said duct.
8. The duct recited in claim 7 further comprising a plurality of actuation ring arms for mounting said actuation ring to said duct.
9. The duct recited in claim 1 in combination with a gas turbine of the type having a compressor and inlet guide vanes for directing flow to the compressor, wherein said variable pitch vanes comprise said inlet guide vanes.
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